巴西专利BR112016010778B1 processing method of a superaustenitic stainless steel alloy

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专利摘要:
METHODS FOR PROCESSING METAL ALLOYS A method of processing an alloy includes heating to a temperature in a working temperature range from a recrystallization temperature of the metal alloy to a temperature below an incipient melting temperature of the metal alloy, and work the league. At least one surface region is heated to a temperature in the working temperature range. The surface region is kept within the working temperature range for a period of time to recrystallize the surface region of the metal alloy, and the alloy is cooled in order to minimize grain growth. In modalities including austenitic and superaustenitic stainless steel alloys, process temperatures and times are selected to avoid deleterious intermetallic sigma phase precipitation. The hot worked superaustenitic stainless steel alloy having equiaxial grains throughout the alloy is also disclosed.
公开号:BR112016010778B1
申请号:R112016010778-0
申请日:2014-10-28
公开日:2021-03-09
发明作者:Robin M. Forbes Jones；Ramesh S. Minisandram
申请人:Ati Properties Llc；
IPC主号:

专利说明:

TECHNOLOGY FUNDAMENTALS TECHNOLOGY FIELD
[001] The present disclosure relates to methods for the thermomechanical processing of metal alloys. DESCRIPTION OF THE FUNDAMENTALS OF TECHNOLOGY
[002] When a metal alloy workpiece, such as, for example, an ingot, a bar, or a raw bar, is thermomechanically processed (ie, hot worked), the workpiece surfaces cool faster than the inside of the workpiece. A specific example of this phenomenon occurs when a metal alloy bar is heated and then forged using a radial forging press or an open die press forge. During hot forging, the grain structure of the metal alloy is deformed due to the action of the molds. If the temperature of the alloy during deformation is lower than the alloy's recrystallization temperature, the alloy will not recrystallize, resulting in a grain structure composed of elongated non-recrystallized grains. If, instead, the temperature of the alloy during deformation is greater than or equal to the recrystallization temperature of the alloy, the alloy will recrystallize in an equiaxial structure.
[003] Since metal alloy workpieces are generally heated to temperatures above the recrystallization temperature of the alloy before hot, the inner portion of the workpiece, which does not cool as fast as the workpiece surfaces work, usually presents a structure completely recrystallized in the hot forge. However, the workpiece surfaces may have a mixture of non-recrystallized grains and completely recrystallized grains due to the lower temperatures on the surfaces resulting from relatively rapid cooling. Representative of this phenomenon, FIG. 1 shows the macrostructure of a radial forged bar from the Datalloy HPTM alloy, a superaustenitic stainless steel alloy available from ATI Allvac, Monroe, NC, USA, showing the non-recrystallized grains in the surface area of the bar. Non-recrystallized grains in the surface region are undesirable because, for example, they increase the noise level during the ultrasonic test, reducing the usefulness of this test. Ultrasonic inspection may be required to check the condition of the alloy workpiece for use in critical applications. Second, non-recrystallized grains reduce the high cycle fatigue strength of the alloy.
[004] Previous attempts to eliminate non-recrystallized grains in the surface region of a thermomechanically processed metal workpiece, such as a forged bar, for example, have proved unsatisfactory. For example, excessive grain growth in the interior portion of the alloy workpieces occurred during treatments to remove unrecrystallized grains from the surface region. Extra large grains can also make ultrasound inspection of metal alloys difficult. Overgrowth in the interior portions can also reduce the fatigue strength of an alloy workpiece to unacceptable levels. In addition, attempts to eliminate non-recrystallized grains in the surface region of a thermomechanically processed alloy workpiece have resulted in the precipitation of harmful intermetallic precipitates, such as, for example, sigma phase (o phase). The presence of these precipitates can decrease resistance to corrosion.
[005] It would be advantageous to develop methods for the thermomechanical processing of metal alloy workpieces in order to minimize or eliminate non-recrystallized grains in a surface region of the workpiece. It would also be advantageous to develop methods for thermomechanical processing of metal alloy workpieces in order to provide an equiaxial recrystallized grain structure through the workpiece cross section, and in which the cross-section is substantially free of harmful intermetallic precipitates. , while limiting the average grain size of the equiaxial grain structure. SUMMARY
[006] According to a non-limiting aspect of the present disclosure, a method of processing a metal alloy comprises heating a metal alloy to a temperature in a working temperature range. The working temperature range is from the recrystallization temperature of the metal alloy to a temperature just below the incipient melting temperature of the metal alloy. The metal alloy is then worked at a temperature in the working temperature range. After working the metal alloy, a surface region of the metal alloy is heated to a temperature in a working temperature range. The surface region of the metal alloy is kept within the working temperature range for a period of time sufficient to recrystallize the surface region of the metal alloy, and to minimize grain growth in the internal region of the metal alloy. The alloy is cooled from the working temperature range to a temperature and cooling rate that minimizes grain growth in the alloy.
[007] In accordance with another aspect of the present disclosure, a non-limiting embodiment of a method of processing a superustenitic stainless steel alloy comprises heating a superaustenitic stainless steel alloy to a temperature in a temperature range of dissolution of intermetallic phase. The dissolution temperature range of the intermetallic phase can be from the solvus temperature of the intermetallic phase to one just below the incipient melting temperature of the superaustenitic stainless steel alloy. In a non-limiting modality, the intermetallic phase is the sigma phase (o phase), composed of Fe-Cr-Ni intermetallic compounds. The superaustenitic stainless steel alloy is maintained in the dissolving temperature range of the intermetallic phase for a sufficient time to dissolve the intermetallic phase and minimize grain growth in the superaustenitic stainless steel alloy. Subsequently, the superaustenitic stainless steel alloy is worked at a temperature in the working temperature range of just above the peak temperature of the time-temperature-transformation curve for the intermetallic phase of the superaustenitic stainless steel alloy, up to just below the incipient melting temperature of the superaustenitic stainless steel alloy. Subsequent to the work, a surface region of the superaustenitic stainless steel alloy is heated to a temperature in an annealing temperature range, where the annealing temperature range is of a temperature just above the apex temperature of the time-temperature curve. -transformation to the intermetallic phase of the alloy until just below the incipient melting temperature of the alloy. The temperature of the superaustenitic stainless steel alloy does not cool until it crosses the time-temperature-transformation curve during the working time of the alloy to heat at least one surface region of the alloy to a temperature in the temperature range of annealing. The surface region of the superaustenitic stainless steel alloy is maintained in the annealing temperature range long enough to recrystallize the surface region, and minimize grain growth in the superaustenitic stainless steel alloy. The alloy is cooled to a temperature and a cooling rate that inhibit the formation of the intermetallic precipitate of the super -ustenitic stainless steel alloy, and minimize the growth of the grain.
[008] According to another non-limiting aspect of the present disclosure, a hot-worked superaustenitic stainless steel alloy comprises, in percentage weight based on the total weight of the alloy, up to 0.2 carbon, up to 20 manganese, 0.1 to 1.0 silicon, 14.0 to 28.0 chromium, 15.0 to 38.0 nickel, 2.0 to 9.0 molybdenum, 0.1 to 3.0 copper, 0 , 08 to 0.9 nitrogen, 0.1 to 5.0 tungsten, 0.5 to 5.0 cobalt, up to 1.0 titanium, up to 0.05 boron, up to 0.05 phosphorus, up to 0.05 sulfur, iron and accidental impurities. The superaustenitic stainless steel alloy includes an equiaxial recrystallized grain structure through a cross section of the alloy, and an average grain size in the range of ASTM 00 to ASTM 3. The equiaxial recrystallized grain structure of the superaustenitic stainless steel alloy worked at hot is substantially free of an intermetallic sigma phase precipitate. BRIEF DESCRIPTION OF THE FIGURES
[009] The characteristics and advantages of the methods, alloys, and articles described in this document can be better understood by reference to the accompanying figures, in which:
[010] FIG. 1 shows a macrostructure of a radial forged bar of the Datalloy HPTM superaustenitic stainless steel alloy, including non-recrystallized grains in a surface region of the bar;
[011] FIG. 2 shows a macrostructure of a radial forged bar of the Datalloy HPTM superaustenitic stainless steel alloy which has been annealed at high temperature (2150 ° F);
[012] FIG. 3 is a flow chart illustrating a non-limiting embodiment of a method for processing a metal alloy in accordance with the present disclosure;
[013] FIG. 4 is an exemplary isothermal transformation curve for a sigma phase intermetallic precipitate in an austenitic stainless steel alloy;
[014] FIG. 5 is a gram flow illustrating a non-limiting embodiment of a method of processing a superaustenitic stainless steel alloy in accordance with the present disclosure;
[015] FIG. 6 is a diagram of process temperature versus time, according to certain non-limiting method modalities of the present disclosure;
[016] FIG. 7 is a diagram of process temperature versus time according to certain non-limiting method embodiments of the present disclosure;
[017] FIG. 8 shows a macrostructure of a mill product comprising the Datalloy HPTM superaustenitic stainless steel alloy processed according to the process temperature versus time diagram of FIG. 6; and
[018] FIG. 9 shows a macrostructure of a mill product comprising the Datalloy HPTM superaustenitic stainless steel alloy processed according to the process temperature versus time diagram of FIG. 7.
[019] The reader will understand the previous details, as well as others, when considering the following detailed description of certain non-limiting modalities, in accordance with the present disclosure. DETAILED DESCRIPTION OF CERTAIN NON-LIMITING MODALITIES
[020] It should be understood that certain descriptions of the modalities described in this document have been simplified to illustrate only those steps, elements, characteristics and / or aspects that are relevant to a clear understanding of the disclosed modalities, while eliminating, for the sake of clarity, other steps , elements, characteristics and / or aspects. Those skilled in the art, after considering the present description of the disclosed modalities, will recognize that other steps, elements and / or characteristics may be desirable in a specific implementation or application of the disclosed modalities. However, since these other steps, elements and / or characteristics can be easily determined and implemented by those skilled in the art after considering the present description of the disclosed modalities, and are therefore not necessary for a complete understanding of the disclosed modalities, a description of these steps, elements and / or characteristics is not provided in this document. As such, it should be understood that the description set out in this document is merely exemplary and illustrative of the disclosed modalities and is not intended to limit the scope of the invention, as defined solely by the claims.
[021] In addition, any numerical range reported in this document is intended to include all sub-ranges included in it. For example, a range of "1 to 10" is intended to include all sub-ranges between (and including) the minimum quoted value of 1 and the maximum quoted value of 10, that is, having a minimum value equal to or greater than 1 and a maximum value equal to or less than 10. Any maximum numerical limitation reported in this document is intended to include all of the lower numerical limitations included in it and any minimum numerical limitation reported in this document is intended to include all of the upper numerical limitations included in it. . Accordingly, depositors reserve the right to change the present disclosure, including the claims, to expressly indicate any sub-band included within the ranges expressly indicated in this document. All of these ranges are intended to be inherently disclosed in this document, such that changes to expressly indicate any sub-ranges would be in accordance with the requirements of 35 U.S.C. § 112, first paragraph, and 35 U.S.C. § 132 (a).
[022] Grammatical articles "one", "one" and "o", if and how used in this document, are intended to include "at least one" or "one or more", unless specified otherwise. Thus, articles are used in this document to refer to one or more of one (that is, at least one) of the article's grammatical objects. As an example, "a component" means one or more components, and thus, possibly, more than one component is contemplated and can be used or used in an implementation of the described modalities.
[023] Any patent, publication or other disclosure material said to be incorporated, in whole or in part, by reference in this document is incorporated in this document only insofar as the incorporated material does not conflict with the definitions, statements or other material of existing disclosure established in this disclosure. As such, and to the extent necessary, disclosure, as set forth in this document, replaces any conflicting material incorporated in this document by reference. Any material, or portion thereof, that is said to be incorporated by reference in this document, but which conflicts with the existing definitions, statements or other disclosure materials set out in this document is only incorporated to the extent that no conflict arises between that material and the existing disclosure material.
[024] This disclosure includes descriptions of various modalities. It should be understood that all the modalities described in this document are exemplary, illustrative and not limiting. Thus, the invention is not limited by the description of the various exemplary, illustrative and non-limiting modalities. Instead, the invention is defined solely by the claims, which can be altered to report any features expressed or inherently described or otherwise expressly or inherently supported by the present disclosure.
[025] It is possible to eliminate the non-recrystallized surface grains in a hot worked metal alloy bar or in another workpiece by carrying out an annealing heat treatment, whereby the alloy is heated to a temperature of annealing that exceeds the recrystallization temperature of the alloy and maintained at the temperature until recrystallization is complete. However, superaustenitic stainless steel alloys and certain other austenitic stainless steel alloys are susceptible to the formation of a deleterious intermetallic precipitate, such as a sigma phase precipitate, when processed in this way. The heating of large size bar and other large mill forms of these alloys to an annealing temperature, for example, can cause harmful intermetallic compounds to precipitate, particularly in a central region of the mill forms. Therefore, annealing times and temperatures must be selected not only to recrystallize the grains from the surface region, but also to dissolve any intermetallic compounds. To ensure that intermetallic compounds are dissolved across the entire cross section of a large bar, for example, it may be necessary to keep the bar at elevated temperature for a significant time. The diameter of the bar is a factor in determining the minimum waiting time required to properly dissolve the harmful intermetallic compounds, but minimum waiting times can be as long as one to four hours, or more. In non-limiting modes, the minimum waiting times are 2 hours, more than 2 hours, 3 hours, 4 hours, or 5 hours. While it may be possible to select a temperature and waiting time that will dissolve the intermetallic compounds and re-crystallize the non-recrystallized grains from the surface region, maintaining the dissolution temperature for long periods can also allow the grains to grow in unacceptably large dimensions. For example, the macrostructure of a radial forged bar of the ATI Datalloy HPTM superaustenitic stainless steel alloy that has been annealed at high temperature (2150 ° F) for a long time is illustrated in FIG. 2. The extra large grains evident in FIG. 2 formed during heating make ultrasonic inspection of the bar difficult to ensure its suitability for certain commercial demand applications. In addition, the extra large grains reduced the fatigue strength of the alloy to unacceptably low levels.
[026] The ATI Datalloy HPTM alloy is generically described in, for example, U.S. Patent Application Serial No. 13 / 331,135, which is incorporated herein by reference in its entirety. The measured chemistry of the ATI Datalloy HPTM superaustenitic stainless steel bar shown in FIG. 2 was, in percentage weight based on the total weight of the alloy: 0.006 carbon; 4.38 manganese; 0.013 phosphorus; 0.0004 sulfur; 0.26 silicon; 21.80 chromium; 29.97 nickel; 5.19 molybdenum; 1.17 copper; 0.91 tungsten; 2.70 cobalt; less than 0.01 titanium; less than 0.01 niobium; 0.04 vanadium; less than 0.01 aluminum; 0.380 nitrogen; less than 0.01 zirconium; equilibrium iron and accidental impurities not detected. In general, the superaustenitic stainless steel alloy ATI Datalloy HPTM comprises, in percentage weight based on the total weight of the alloy, up to 0.2 carbon, up to 20 manganese, 0.1 to 1.0 silicon, 14.0 to 28.0 chromium, 15.0 to 38.0 nickel, 2.0 to 9.0 molybdenum, 0.1 to 3.0 copper, 0.08 to 0.9 nitrogen, 0.1 to 5.0 tungsten, 0.5 to 5.0 cobalt, up to 1.0 titanium, up to 0.05 boron, up to 0.05 phosphorus, up to 0.05 sulfur, iron, and accidental impurities.
[027] Referring to FIG. 3, in accordance with an aspect of this disclosure, certain steps of a non-limiting embodiment 10 of a method of processing a metal alloy are shown schematically. Method 10 can comprise heating 12 a metal alloy to a temperature in a working temperature range. The working temperature range can be from the re-crystallization temperature of the metal alloy to a temperature just below an incipient melting temperature of the metal alloy. In a non-limiting mode of method 10, the metal alloy is the Datalloy HPTM superaustenitic stainless steel alloy and the working temperature range is greater than 1900 ° F to 2150 ° F. Additionally, when the metal alloy is a superaustenitic stainless steel alloy or other austenitic stainless steel alloy, the alloy is preferably heated to a temperature within the working temperature range that is high enough to dissolve the precipitated intermetallic phases present in the alloy. .
[028] Once heated to a temperature within the working temperature range, the metal alloy is worked 14 within the working temperature range. In a non-limiting mode, the work of the metal alloy within a working temperature range results in the recrystallization of the grains from at least one internal region of the metal alloy. Since the surface region of the metal alloy tends to cool faster due, for example, to cooling by contact with the working molds, the grains in the surface region of the metal alloy can cool below the working temperature range and may not recrystallize while working. In various non-limiting embodiments in this document, a "surface region" of an alloy or metal alloy workpiece refers to a region of the surface at a depth of 0.001 inch, 0.01 inch, 0.1 pole-gada, or 1 inch or more into the alloy or workpiece. It should be understood that the depth of a surface region, which does not recrystallize during work 14, depends on several factors, such as, for example, the composition of the metal alloy, the temperature of the alloy at the beginning of the work, the diameter or thickness of the alloy, the temperature of the working molds, and the like. The depth of a surface region that does not recrystallize during work is easily determined by one skilled in the art without undue experimentation and, as such, the surface region that does not recrystallize in any specific modality not limiting the method of the present disclosure does not needs to be discussed later in this document.
[029] Since a surface region cannot be recrystallized during work, subsequent to the work of the alloy, and before any intentional cooling of the alloy, at least the surface region of the alloy is heated 18 to a temperature in the range working temperature. Optionally, after working 14 of the metal alloy, the alloy is transferred 16 to a heating device. In various non-limiting embodiments, the heating apparatus comprises at least one of an oven, a flame heating station, an induction heating station, or any other suitable heating apparatus known to a person skilled in the art. It will be recognized that a heating apparatus may be in place at the workstation, or molds, rollers, or any other hot working apparatus at the workstation may be heated to minimize cooling of the contacting surface region of the alloy during the work.
[030] After at least the surface region of the metal alloy is heated 18 within the working temperature range, the temperature of the surface region is maintained 20 in the working temperature range for a period of time sufficient to recrystallize the working region. surface of the metal alloy, so that the entire cross-section of the metal alloy is recrystallized. As applied to superaustenitic stainless steel alloys and austenitic alloys, the temperature of the superaustenitic stainless steel or austenitic stainless steel alloy does not cool to cross the time-temperature-transformation curve during the work time period 14 of the alloy to heating 18 of at least one surface region of the alloy at a temperature in the annealing temperature range. This prevents harmful intermetallic phases, such as, for example, sigma phase, from precipitating in the superaustenitic stainless steel or austenitic alloy. This limitation is explained below. In certain non-limiting modalities of the methods according to the present disclosure applied to superaustenitic stainless steel alloys and other austenitic stainless steel alloys, the period of time during which the temperature of the heated surface region is maintained within the temperature range Annealing time is sufficient time to recrystallize the grains in the surface region and dissolve any deleterious intermetallic precipitate phases.
[031] After keeping the metal alloy in the working temperature range 20 to recrystallize the surface region of the alloy, the alloy is cooled 22. In certain non-limiting modalities, the metal alloy can be cooled to room temperature. In certain non-limiting modalities, the metal alloy can be cooled from the working temperature range to a cooling rate and up to a temperature sufficient to minimize grain growth in the metal alloy. In a non-limiting mode, a cooling rate during the cooling step is in the range of 0.3 degrees Fahrenheit per minute to 10 degrees Fahrenheit per minute. Exemplary methods of cooling, in accordance with the present disclosure, include, but are not limited to, temperament (such as, for example, water temperament and oil temperament), forced air cooling, and air cooling. It will be recognized that a cooling rate that minimizes grain growth in the alloy will be dependent on many factors, including, but not limited to, composition of the alloy, the initial working temperature, and the diameter or thickness of the alloy. Combining the heating steps 18 of at least one surface region of the metal alloy with the working and maintenance temperature range 20 of the surface region within the working temperature range for a period of time to recrystallize the surface region can referred to in this document as "quick annealing (flash)".
[032] As used in this document in connection with the present methods, the term "metal alloy" encompasses materials that include a predominant metal base or element, one or more intentional alloy additions, and accidental impurities. As used herein, "metal alloy" includes "commercially pure" materials and other materials that consist of a metal element and accidental impurities. The present method can be applied to any suitable metal alloy. According to a non-limiting modality, the method according to the present disclosure can be carried out on a metallic alloy selected from a superaustenitic stainless steel alloy, an austenitic stainless steel alloy, a titanium alloy, a commercially pure titanium, a nickel alloy, a nickel-based superalloy, and a cobalt alloy. In a non-limiting embodiment, the metal alloy comprises an austenitic material. In a non-limiting modality, the metal alloy comprises one of a superaustenitic stainless steel alloy and an austenitic stainless steel alloy. In another non-limiting modality, the metal alloy comprises a superaustenitic stainless steel alloy. In certain non-limiting modalities, an alloy processed by a method of the present disclosure is selected from the following alloys: ATI Datalloy HPTM alloy (UNS not assigned); alloy ATR ATI Datalloy 2® (UNS not assigned); Alloy 25-6HN (UNS N08367); Alloy 600 (UNS N06600); alloy Hastelloy®G-2TM (UNS N06975); Alloy 625 (UNS N06625); League 800 (UNS N08800); Alloy 800H (UNS N08810), Alloy 800AT (UNS N08811); Alloy 825 (UNS N08825); Alloy G3 (UNS N06985); Alloy 2535 (UNS N08535); Alloy 2550 (UNS N06255); and Alloy 316L (UNS S31603).
[033] The ATR Datalloy 2® ESR alloy is available from ATI Allvac, Monroe, North Carolina, USA, and is described generically in International Patent Application Publication No. WO 99/23267, which is incorporated into this document by reference in its entirety. The ESR ATI Datalloy 2® alloy has the following nominal chemical composition, in percentage weight based on the total weight of the alloy: 0.03 carbon; 0.30 silicon; 15.1 manganese; 15.3 chromium; 2.1 molybdenum; 2.3 nickel; 0.4 nitrogen; and balance iron and accidental impurities. In general, the ATI Datalloy 2® alloy comprises, in percentage weight based on the total weight of the alloy: up to 0.05 carbon; up to 1.0 silicon; 10 to 20 manganese; 13.5 to 18.0 chromium; 1.0 to 4.0 nickel; 1.5 to 3.5 molybdenum; 0.2 to 0.4 nitrogen; iron; and accidental impurities.
[034] Superaustenitic stainless steel alloys do not fit the classic definition of stainless steel because iron constitutes less than 50 percent by weight of superaustenitic stainless steel alloys. In comparison to conventional austenitic stainless steels, superaustenitic stainless steel alloys have superior resistance to corrosion and crevice corrosion in environments containing halides.
[035] The working step of a metal alloy at an elevated temperature according to the present method can be performed using any known technique. As used in this document, the terms "forming", "forging" and "radial forging" refer to thermomechanical processing ("TMP"), which can also be referred to in this document as "thermomechanical work" or simply "work". As used in this document, unless otherwise specified, "work" refers to "hot work". "Hot work", as used in this document, refers to a controlled mechanical operation to mold a metal alloy at temperatures equal to or above the recrystallization temperature of the metal alloy. Thermo-mechanical work covers a series of metal alloy forming processes that combine controlled heating and deformation to obtain a synergistic effect, such as improved strength, without loss of stiffness. See, for example, ASM Materials Engineering-Neering Dictionary, J. R. Davis, ed., ASM International (1992), p. 480.
[036] In various non-limiting modalities of method 10 in accordance with the present disclosure, and with reference to FIG. 3, the metal alloy work 14 comprises at least one of the forging, rolling, roughing, extrusion, and forming, of the metal alloy. In several more specific non-limiting modalities, the alloy 14 work comprises the forging of the alloy. Several non-limiting modalities can comprise the work 14 of the metal alloy using at least one forging technique selected from forging with lamination, stamping, cogging, open mold forging, printing forge, press forging, forging a automatic hot, radial forging, and repression forging. In a non-limiting mode, heated molds, heated rollers and / or the like can be used to reduce the cooling of a surface region of the metal alloy during work.
[037] In certain non-limiting modalities of the methods according to the present disclosure, and again referring to FIG. 3, heating a surface region 18 of the metal alloy to a temperature within the working temperature range may comprise heating the surface region by arranging the alloy in an annealing furnace or other type of furnace. In certain non-limiting modalities of the methods according to the present disclosure, heating a surface region 18 to the working temperature range comprises at least one of oven heating, flame heating, and induction heating.
[038] In certain non-limiting modalities of the methods according to the present disclosure, and again referring to FIG. 3, maintaining the surface region of the metal alloy within the working temperature range may comprise maintaining the surface region within the working temperature range for a period of time sufficient to recrystallize the heated surface region of the alloy, and to minimize grain growth in the metal alloy. In order to avoid the growth of grains in the excessively large metal alloy, for example, in certain non-limiting modalities, the period of time during which the temperature of the surface region is kept within the temperature range of The work may be limited to a period of time not longer than is necessary to recrystallize the region of the heated surface from metal alloy, resulting in recrystallized grains across the entire cross section of the metal alloy. In other non-limiting embodiments, maintenance 20 comprises keeping the metal alloy in the working temperature range for a period of time sufficient to allow the temperature of the metal alloy to equalize from the surface to the center of the shape of the metal alloy. In specific non-limiting modalities, the metal alloy is kept 20 in the working temperature range for a period of time in the range of 1 minute to 2 hours, 5 minutes to 60 minutes, or 10 minutes to 30 minutes.
[039] Additionally, in the non-limiting modalities of the present methods applied to superaustenitic stainless steel alloys and austenitic stainless steel alloys, the alloy is preferably worked 14, the heated surface region 18, and the alloy maintained 20 at temperatures within the working temperature range that are high enough to maintain the intermetallic phases that are detrimental to the mechanical or physical properties of the alloys in the solid solution, or to dissolve any intermetallic phases precipitated in the solid solution during these steps. In a non-limiting modality, the maintenance of the intermetallic phases in the solid solution comprises preventing the temperature of the super-susceptible stainless steel alloy and of the austenitic stainless steel alloy from cooling to cross the time-temperature-transformation curve during the time period alloy working to heat at least one surface region of the alloy to a temperature in the annealing temperature range. This is explained further below. In certain non-limiting modalities of the methods according to the present disclosure applied to superaustenitic stainless steel alloys and austenitic stainless steel alloys, the period of time during which the temperature of the heated surface region is maintained within the temperature range working time is sufficient time to recrystallize the grains in the surface region, dissolve any deleterious intermetallic precipitate phases that may have precipitated during work step 14 due to unintentional cooling of the surface region during work 14, and minimize the growth of the grain in the alloy. It will be recognized that the length of that time period depends on factors that include the composition of the metal alloy and the dimensions (for example, diameter or thickness) of the shape of the metal alloy. In certain non-limiting embodiments, the surface region of the metal alloy can be maintained within the working temperature range for a period of time in the range of 1 minute to 2 hours, 5 minutes to 60 minutes, or 10 minutes to 30 minutes.
[040] In certain non-limiting modalities of the methods according to the present disclosure in which the metal alloy is one of a superaustenitic stainless steel and austenitic stainless steel alloy, heating 12 comprises heating to a working temperature range from the solvus temperature of the intermetallic precipitate phase to just below the incipient melting temperature of the metal alloy. In certain non-limiting modalities of the methods according to the present disclosure in which the metal alloy is one of a superaustenitic stainless steel and austenitic stainless steel alloy, the working temperature range during the metal alloy working step 14 is from a temperature just below the solvus temperature of an intermetallic sigma phase precipitate of the metal alloy to a temperature just below the incipient melting temperature of the metal alloy.
[041] Without pretending to be bound by any specific theory, it is believed that intermetallic precipitates are formed mainly in alloys of austenitic stainless steel and superaustenitic stainless steel alloys because the pre-precipitation kinetics is fast enough to allow the precipitation occurs in the alloy as the temperature of any portion of the alloy cools to a temperature equal to or less than the temperature of the tip, or apex, of the isothermal transformation curve of the alloy for the precipitation of a specific intermetallic phase. FIG. 4 is an exemplary isothermal transformation curve 40, also known as a time-temperature-transformation diagram or curve (a "TTT diagram" or a "TTT curve"). FIG. 4 predicts the kinetics for 0.1 weight percent of intermetallic precipitation of sigma phase (o phase) in an exemplary austenitic stainless steel alloy. It will be seen by FIG. 4 that intermetallic precipitation occurs more quickly, that is, in the shortest time, at the apex 42 or "tip" of the "C" curve that comprises the isothermal transformation curve 40. In this sense, in a non-limiting modality of the methods according with the present disclosure, with reference to the working temperature range, the phrase "just above the apex temperature" of an intermetallic sigma phase precipitate of the metal alloy refers to a temperature that is just above the apex 42 temperature of the curve C of the TTT diagram for the specific alloy. In other non-limiting modalities, the phrase "a temperature just above the apex temperature" refers to a temperature that is in the range of 5 degrees Fahrenheit, or 10 degrees Fahrenheit, or 20 degrees Fahrenheit, or 30 degrees Fahrenheit, or 40 degrees Fahrenheit, or 50 degrees Fahrenheit above the apex 42 temperature of the metal alloy intermetallic sigma precipitate.
[042] When the methods according to the present disclosure are conducted in austenitic stainless steel alloys or superaustenitic stainless steel alloys, the cooling step 22 of the metallic alloy may comprise cooling at a rate sufficient to inhibit the precipitation of an intermetallic sigma phase precipitate in the metal alloy. In a non-limiting mode, a cooling rate is in the range of 0.3 degrees Fahrenheit per minute to 10 degrees Fahrenheit per minute. Exemplary methods of cooling, in accordance with the present disclosure, include, but are not limited to, temperament, such as, for example, water temperament and oil temperament, forced air cooling, and air cooling.
[043] Specific examples of austenitic materials that can be processed using the methods according to the present disclosure include, but are not limited to: ATI Datalloy HPTM alloy (UNS not assigned); alloy ATR ATI Datalloy 2® (UNS not assigned); Alloy 25-6HN (UNS N08367); Alloy 600 (UNS N06600); alloy Hastelloy®G-2TM (UNS N06975); Alloy 625 (UNS N06625); League 800 (UNS N08800); Alloy 800H (UNS N08810), Alloy 800AT (UNS N08811); Alloy 825 (UNS N08825); Alloy G3 (UNS N06985); Alloy 2550 (UNS N06255); Alloy 2535 (UNS N08535); and Alloy 316L (UNS S31603).
[044] Referring now to FIGS. 5-7, in accordance with one aspect of the present disclosure, a non-limiting embodiment of a method 50 of processing one of a superaustenitic stainless steel alloy and an austenitic stainless steel alloy is shown in the flowchart of FIG. 5 and in the time-temperature diagrams of FIGS. 6 and 7. It should be recognized that the description below of a non-limiting mode of a method 50 also applies to superaustenitic stainless steel alloys, austenitic stainless steel alloys, and other austenitic materials. For the sake of simplicity, FIG. 5 refers only to superaustenitic stainless steels. In addition, although FIGS. 6 and 7 are time-temperature graphs of the methods applied to the Datalloy HPTM alloy, a superaustenitic stainless steel alloy, similar process steps, which generally use different temperatures, are applicable to austenitic stainless steel alloys and other materiaisaustenitic alloys.
[045] Method 50 comprises heating 52 and a superaustenitic stainless steel alloy, for example, at a temperature in an intermetallic phase precipitate dissolution temperature range from the solvus temperature of the intermetallic phase precipitate in the steel alloy superaustenitic stainless steel up to a temperature just below the incipient melting temperature of the superaustenitic stainless steel alloy. In a specific non-limiting method modality for the Datalloy HPTM alloy, the temperature range for the dissolution of intermetallic precipitate is greater than 1900 ° F to 2150 ° F. In a non-limiting modality, the intermetallic phase is the sigma phase (o phase), which is composed of Fe-Cr-Ni intermetallic compounds.
[046] The superaustenitic stainless steel alloy is maintained 53 in the intermetallic phase precipitate dissolution temperature range for a time sufficient to dissolve the precipitates of the intermetallic phase, and to minimize grain growth in the superaustenitic stainless steel alloy. . In non-limiting modalities, a superaustenitic stainless steel alloy or an austenitic stainless steel alloy can be kept in the temperature range of the intermetallic precipitate dissolution for a period of time in the range of 1 minute to 2 hours, 5 minutes 60 minutes, or 10 minutes to 30 minutes. It will be recognized that the minimum time required to maintain a superaustenitic stainless steel alloy or austenitic stainless steel alloy in the intermetallic phase precipitate dissolution temperature range to dissolve the intermetallic phase precipitate depends on factors, including, for example , the composition of the alloy, the thickness of the workpiece, and the specific temperature in the temperature range of the metal phase precipitate that is applied. It should be understood that one skilled in the art, after considering the present disclosure, could determine the minimum time required for the dissolution of the intermetallic phase without undue experimentation.
[047] After maintenance step 53, the superaustenitic stainless steel alloy is worked 54 at a temperature in a working temperature range from just above the summit temperature of the TTT curve for the intermetallic phase precipitate of the alloy to just below the alloy's incipient melting temperature.
[048] Since a surface region cannot be recrystallized during work 54, subsequent to the work of the superaustenitic stainless steel alloy, and before any intentional cooling of the alloy, at least one surface region of the superaustenitic stainless steel alloy 58 is heated to a temperature in the annealing temperature range. In a non-limiting mode, the annealing temperature range is from a temperature just above the summit temperature (see, for example, FIG. 4, point 42) of the time-temperature-transformation curve for the intermetallic phase precipitate of the alloy superaustenitic stainless steel up to just below the incipient melting temperature of the superaustenitic stainless steel alloy.
[049] Optionally, after the 54 work of the superaustenitic stainless steel alloy, the superaustenitic stainless steel alloy can be transferred 56 to a heating device. In various non-limiting embodiments, the heating apparatus comprises at least one of an oven, a flame heating station, an induction heating station, or any other suitable heating apparatus known to a person skilled in the art. For example, a heating apparatus may be in place at the workstation, or molds, rollers, or any hot working apparatus at the workstation may be heated to minimize unintended cooling of the contact surface area of the metal alloy. .
[050] Subsequent to work 54, a surface region of the alloy is heated 58 to a temperature in an annealing temperature range. In the heating step 58, the annealing temperature range is from a temperature just above the summit temperature (see, for example, FIG. 4, point 42) of the time-temperature-transformation curve for the intermetallic phase precipitate of the superaustenitic stainless steel alloy up to just below the alloy's incipient melting temperature. The temperature of the superaustenitic stainless steel alloy does not cool to cross the time-temperature-transformation curve during the time period of the work 54 of the alloy to heating 58 of at least one surface region of the alloy at a temperature in the temperature range of annealing. However, it will be recognized that since the surface region of a super-austenitic stainless steel alloy cools down faster than the inner region of the alloy, there is a risk that the surface region of the alloy will cool below the range annealing temperature during work 54, resulting in the precipitation of intermetallic phase precipitates in the surface region.
[051] In a non-limiting modality, with reference to FIGS. 5-7, the surface region of the superaustenitic stainless steel alloy is maintained in the annealing temperature range for a period of time sufficient to recrystallize the surface region of the superaustenitic stainless steel alloy, and dissolve any deleterious intermetallic precipitate phases. that may have precipitated in the surface region, while not resulting in excessive growth of the grain in the alloy.
[052] Referring again to FIGS. 5-7, subsequent to maintaining the alloy 60 in the annealing temperature range, the alloy is cooled 62 at a cooling rate and at a temperature sufficient to inhibit the formation of the intermetallic sigma phase precipitate in the superaustenitic stainless steel alloy. In a non-limiting embodiment of method 50, the temperature of the alloy in cooling 62 of the alloy is a temperature that is less than the temperature of the apex of curve C of a TTT diagram for the specific austenitic alloy. In another non-limiting mode, the temperature of the alloy in the cooling 62 is the ambient temperature.
[053] Another aspect of this disclosure is directed to certain alloy mill products. Certain alloy mill products according to the present disclosure comprise or consist of a metal alloy that has been processed by any of the methods according to the present disclosure, and which has not been processed to remove a non-recrystalline surface region - used by grinding or other mechanical material removal technique. In certain non-limiting modalities, a metal alloy mill product according to the present disclosure comprises or consists of an austenitic stainless steel alloy or a superaustenitic stainless steel alloy that has been processed by any of the methods of accordance with this disclosure. In certain non-limiting embodiments, the metal alloy grain structure of the metal alloy mill product comprises an equiaxial recrystallized grain structure through a metal alloy cross section, and an average grain size of the metal alloy is in a number range. ASTM grain size from 00 to 3, or 00 to 2, or 00 to 1, as measured according to ASTM Designation E112 - 12. In a non-limiting embodiment, the structure of equiaxial recrystallized grains from the metal alloy is substantially free of a precipitate of intermetallic sigma phase.
[054] According to certain non-limiting modalities, a metal alloy mill product according to the present invention comprises or consists of a superaustenitic stainless steel alloy or an austenitic stainless steel alloy having a recrystallized grain structure equiaxial to the along a cross section of the mill product, where an average grain size of the alloy is in an ASTM grain size number range from 00 to 3 or 00 to 2 or 00 to 1, or 3 to 4, or a number of ASTM grain size greater than 4, as measured according to ASTM designation E112 - 12. In a non-limiting embodiment, the equiaxial recrystallized grain structure of the alloy is substantially free of an intermetallic sigma phase precipitate.
[055] Examples of metal alloys that can be included in a metal alloy mill product according to this invention include, but are not limited to, any of the ATI Datalloy HPTM alloy (UNS not assigned); ESR alloy ATI Datalloy 2® (UNS not assigned); Alloy 25-6HN (UNS N08367); Alloy 600 (UNS N06600); ® G -2TM (UNS N06975); Alloy 625 (UNS N06625); League 800 (UNS N08800); Alloy 800H (UNS N08810), Alloy 800AT (UNS N08811); Alloy 825 (UNS N08825); Alloy G3 (UNS N06985); Alloy 2.535 (UNS N08535); 2.550 alloy (UNS N06255); Alloy 2.535 (UNS N08535); and Alloy 316L (UNS S31603).
[056] With respect to different aspects of the present disclosure, it is envisaged that the grain size of metal alloy bars or other metal alloy mill products made in accordance with various non-limiting modalities of the methods of the present disclosure may be adjusted by changing temperatures used in the various steps of the method. For example, and without limitation, the grain size in a center region of an alloy bar or otherwise can be reduced by lowering the temperature at which the alloy is worked in the method. A possible method for achieving grain size reduction includes heating a metal alloy form worked at a temperature high enough to dissolve any deleterious intermetallic precipitates formed during the previous processing steps. For example, in the case of HP DatalloyTM alloy, the alloy can be heated to a temperature of about 2100 ° F, which is a temperature higher than the solvus line temperature of the sigma phase of the alloy. The sigma-solvus temperature of superaustenitic stainless steels that can be processed as described in this document is typically in the range of 1600 ° F to 1800 ° F. The alloy can then be immediately cooled to a working temperature of, for example , about 2050 ° F for the Datalloy HPTM alloy, without letting the temperature drop below the vertex temperature of the TTT diagram for the sigma phase. The alloy can be hot worked, for example, by radial forging, to a desired diameter, followed by immediate transfer to a furnace to allow the recrystallization of unrecreated surface grains, without allowing the processing time to enter the temperature solvus and the summit temperature of the TTT diagram exceeds the time for the summit TTT, either without letting the temperature drop below the apex of the TTT diagram for the sigma phase during this period, or so that the temperature of the stainless steel alloy superaustenitic does not cool down to intersect the time-temperature-transformation curve during the working time of the alloy to heat at least one surface region of the alloy to a temperature in the annealing temperature range. The alloy can then be cooled from the recrystallization step to a temperature and cooling rate that inhibit the formation of harmful intermetallic precipitates in the alloy. A sufficiently fast cooling speed can be achieved, for example, by water extinguishing the alloy.
[057] The following examples are intended to further describe certain non-limiting modalities, without restricting the scope of the present invention. Persons ordinarily skilled in the art will appreciate that the variations of the examples which follow are possible within the scope of the invention, which is defined only by the claims. EXAMPLE 1
[058] A 20-inch diameter ingot of the HP DatalloyTM alloy, available from ATI Allvac, was prepared using a conventional fusion technique combining decarbonization with argon and oxygen and electroslag remelting steps. The ingot had the following chemical measured, in percent by weight based on the total weight of the alloy: 0.007 carbon; 4.38 manganese; 0.015 phosphorus; less than 0.0003 sulfur; 0.272 silicon; 21.7 chromium; 30.11 nickel; 5.23 molybdenum; 1.17 copper; equilibrium iron and unmeasured accidental impurities. The ingot was homogenized at 2200 ° F and turned and pulled with several reheats in an open die forging press to a diameter of 12.5 inch raw bars. The forged raw bar was further processed by the following steps, which can be followed with reference to FIG. 6. The 12.5-inch diameter raw bar has been heated (see, for example, Fig. 5, step 52) to a precipitated dissolution temperature of 2200 ° F intermetallic phase, which is a temperature in the temperature range of dissolution of intermetallic phase precipitate, according to the present disclosure, and kept (53) at temperature for more than 2 hours to convert any sigma phase intermetallic precipitates into solution. The raw bar was cooled to 2100 ° F, which is a temperature in a working temperature range, according to the present disclosure, and then forged in radial (54) to a raw bar with a diameter of 9, 84 inches. The raw bar was immediately transferred (56) to an oven set at 2100 ° F, which is a temperature in a range of annealing temperatures for this alloy in accordance with the present disclosure, and at least one surface region of the alloy was heated (58) to the annealing temperature. The raw bar was kept in the oven for 20 minutes, so that the temperature of the surface region is maintained (60) in the annealing temperature range for a period of time sufficient to recrystallize the surface region and dissolve any deleterious precipitated intermetallic phases in the surface region, without resulting in excessive grain growth in the alloy. The raw bar was cooled (62) by tempering in water at room temperature. The resulting macrostructure through a cross section of the raw bar is shown in FIG. 8. The macrostructure shown in FIG. 8 does not show any evidence of unrecrystallized grains in the outer perimeter region (ie, in a surface region) of the forged bar. The ASTM grain size number of the equiaxial grain is between ASTM 0 and 1. EXAMPLE 2
[059] A 20-inch diameter ingot of the HP DatalloyTM alloy, available from ATI Allvac, was prepared using a conventional fusion technique combining decarbonization with argon and oxygen and electro-sludge remelting steps. The ingot had the following chemical measured, in percentage by weight based on the total weight of the alloy: 0.006 carbon; 4.39 manganese; 0.015 phosphorus; less than 0.0004 sulfur; 0.272 silicon; 21.65 chromium; 30.01 nickel; 5.24 molybdenum; 1.17 copper; equilibrium iron and unmeasured accidental impurities. The ingot was homogenized at 2200 ° F and turned and pulled with several reheats in an open die forging press to a diameter of 12.5 inch raw bars. The raw bar has been subjected to the following process steps, which can be followed by reference to FIG. 7. The 12.5-inch raw bar was heated (see, for example, Fig. 5, step 52) to 2100 ° F, which is a temperature in the temperature range of the intermetallic phase precipitate dissolution, from according to the present disclosure, and kept (53) at temperature for more than 2 hours to convert any sigma phase intermetallic precipitates into solution. The raw bar was cooled to 2050 ° F, which is a temperature in a working temperature range, according to the present disclosure, and then forged in radial (54) to a 9.84 inch diameter raw bar . The crude bar was immediately transferred (56) to an oven set at 2050 ° F, which is a temperature in the annealing temperature range for this alloy in accordance with the present disclosure, and at least one surface region of the alloy was heated (58) to the annealing temperature. The crude bar was kept in the oven for 45 minutes, so that the temperature of the surface region is maintained (60) in the annealing temperature range for a period of time sufficient to recrystallize the surface region and dissolve any deleterious intermetallic precipitated phases. in the surface region, without resulting in excessive grain growth in the alloy. The raw bar was cooled (62) by extinction in water at room temperature. The resulting macrostructure through a cross section of the raw bar is shown in FIG. 9. The macrostructure shown in FIG. 9 shows no evidence of unrecrystallized grains in the outer perimeter region (ie, in a surface region) of the forged bar. The ASTM grain size number of the equiaxial grain is ASTM 3. EXAMPLE 3
[060] A 20-inch diameter ingot of ATI Allvac AL-6XN® austenitic stainless steel alloy (UNS N08367) is prepared using a conventional fusion technique, combining decarbonization with argon and oxygen and electro-sludge melting steps . The ingot has the following chemical measured, in percentage by weight based on the total weight of the alloy: 0.02 carbon; 0.30 manganese; 0.020 phosphorus; 0.001 sulfur; 0.35 silicon; 21.8 chromium; 25.3 nickel; 6.7 molybdenum; 0.24 nitrogen; 0.2 copper; equilibrium iron and unmeasured accidental impurities. The following process steps can be better understood with reference to FIG. 6. The ingot is heated (52) to 2300 ° F, which is a temperature in the intermetallic phase precipitate dissolution temperature range, according to the present disclosure, and kept (53) at temperature for 60 minutes to transform into any sigma phase intermetallic precipitates. The ingot is cooled to 2200 ° F, which is a temperature in a working temperature range, and then hot rolled (54) onto a 1-inch-thick plate. The plate is immediately transferred (56) to an annealing oven set at 2050 ° F and at least one surface region of the plate is heated (58) to the annealing temperature. The annealing temperature is in an annealing temperature range of a temperature immediately above the apex temperature of the time-temperature-transformation curve of the austenitic stainless steel alloy intermetallic sigma phase slightly below the incipient melting temperature of the steel alloy austenitic stainless steel. The plate does not cool to a temperature that intersects the time-temperature-transformation diagram for the sigma phase during hot rolling (54) and transfer steps (56). The surface region of the alloy is maintained (60) in the annealing temperature range for 15 minutes, which is sufficient to recrystallize the surface region and to dissolve any deleterious intermetallic precipitate phases, while not resulting in excessive grain growth in a region alloy surface. The alloy is then cooled (62) by quenching with water, which provides a sufficient cooling rate to inhibit the formation of intermetallic sigma phase precipitate in the alloy. The macrostructure does not show any evidence of grains not recrystallized in the surface region of the laminated plate. The ASTM grain size number of the equiaxial grain is ASTM 3. EXAMPLE 4
[061] A 20-inch diameter ingot of Grade 316L austenitic stainless steel alloy (UNS S31603) is prepared using a conventional fusion technique, combining decarbonization with argon and oxygen and electroslag remelting steps. The ingot has the following chemical measured, in percentage by weight based on the total weight of the alloy: 0.02 carbon; 17.3 chromium; 12.5 nickel; 2.5 molybdenum; 1.5 manganese; 0.5 silicon, 0.035 phosphorus; 0.01 sulfur; iron balance and other accidental impurities. The following process steps can be better understood with reference to FIG. 3. The metal alloy is heated (12) to 2190 ° F, which is within the working temperature range of the alloy, that is, a range of a recrystallization temperature of the alloy slightly below the incipient melting temperature of the alloy. The heated ingot is worked (14). Specifically, the heated ingot is turned and pulled with various reheats in an open die forging press to a diameter of 12.5-inch raw bars. The ingot is reheated to 2190 ° F and radially forged (14) to a 9.84 inch diameter bar. The raw bar is transferred (16) to an annealing furnace set at 2048 ° F. The furnace temperature is in an annealing temperature range, which is a range of alloy recrystallization temperature slightly below the incipient melting temperature of the turns on. A surface region of the alloy is maintained (20) at the annealing temperature for 20 minutes, which is sufficient retention time to recrystallize the surface region of the alloy. The alloy is then cooled by quenching with water at room temperature. water extinction provides sufficient cooling speed to minimize grain growth in the alloy. EXAMPLE 5
[062] A 20-inch diameter ingot of the 2535 alloy (UNS N08535), available from ATI Allvac, was prepared using a conventional fusion technique combining decarbonization with argon and oxygen and electro-scorching remelting steps. The ingot was homogenized at 2200 ° F and turned and pulled with various reheats in an open die forging press to a diameter of 12.5 inch raw bars. The 12.5-inch raw bar was heated (see, for example, Fig. 5, step 52) to a precipitated dissolution temperature of 2100 ° F intermetallic phase, which is a temperature in the dissolution temperature range of precipitate of intermetallic phase, according to the present disclosure, and kept (53) at temperature for more than 2 hours to transform into solution any intermetallic precipitates of sigma phase. The raw bar was cooled to 2050 ° F, which is a temperature in a working temperature range, according to the present disclosure, and then it is forged in radial (54) to a 9.84 diameter raw bar inches. The raw bar was immediately transferred (56) to an oven set at 2050 ° F, which is a temperature in the annealing temperature range for this alloy according to the present disclosure. The raw bar temperature does not cool down to intersect the time-temperature-transformation diagram for the sigma phase in the alloy during the forging and transfer time period. At least one surface region of the alloy is heated (58) to the annealing temperature. The raw bar was kept in the oven for 45 minutes, so that the temperature of the surface region is maintained (60) in the annealing temperature range for a period of time sufficient to recrystallize the surface region and dissolve any deleterious intermetallic precipitated phases. in the surface region, without resulting in excessive grain growth in the alloy. The raw bar was cooled (62) by tempering in water at room temperature. The macrostructure exhibits no evidence of non-recrystallized grains on the outer perimeter (ie, in the surface region) of the forged bar. The ASTM grain size number of the equiaxial grain is ASTM 2. EXAMPLE 6
[063] A 20-inch diameter ingot of the 2550 alloy (UNS N06255), available from ATI Allvac, was prepared using a conventional fusion technique combining decarbonization with argon and oxygen and electro-scorching remelting steps. The ingot was homogenized at 2200 ° F and turned and pulled with various reheats in an open die forging press to a diameter of 12.5 inch raw bars. The 12.5-inch raw bar was heated (see, for example, Fig. 5, step 52) to a precipitated dissolution temperature of 2100 ° F intermetallic phase, which is a temperature in the dissolution temperature range of precipitate of intermetallic phase, according to the present disclosure, and kept (53) at temperature for more than 2 hours to transform into solution any intermetallic precipitates of sigma phase. The raw bar was cooled to 1975 ° F, which is a temperature in a working temperature range, according to the present disclosure, and then it is radially forged (54) to a 9.84 diameter raw bar inches. The raw bar was immediately transferred (56) to an oven set at 1975 ° F, which is a temperature in the annealing temperature range for this alloy in accordance with the present disclosure, and at least one surface region of the alloy was heated (58) to the annealing temperature. The raw bar temperature does not cool to intersect the time-temperature-transformation diagram for the sigma phase in the alloy during the forging and transfer time period. The raw bar was kept in the oven for 75 minutes, so that the temperature of the surface region is maintained (60) in the annealing temperature range for a period of time sufficient to recrystallize the surface region and dissolve any precipitated phases. harmful intermetallic in the su-perficial region, without resulting in excessive grain growth in the alloy. The raw bar was cooled (62) by tempering in water at room temperature. The macrostructure exhibits no evidence of non-recrystallized grains on the outer perimeter (ie, in the surface region) of the forged bar. The ASTM grain size number of the equiaxial grain is ASTM 3.
[064] It will be understood that the present description illustrates those aspects of the invention relevant to a clear understanding of the invention. Certain aspects that would be evident to those ordinarily skilled in the art and, therefore, would not facilitate a better understanding of the present invention, have not been presented in order to simplify the present description. Although only a limited number of embodiments of the present invention are necessarily described in this document, a person ordinarily skilled in the art will, in considering the foregoing description, recognize that many modifications and variations of the present invention can be employed. All such variations and modifications of the present invention are intended to be covered by the preceding description and the following claims.

权利要求:
Claims (12)
[0001]
1. Method of processing a superaustenitic stainless steel alloy, in which the superaustenitic stainless steel alloy comprises less than 50 weight percent iron based on the total weight of the alloy, the method CHARACTERIZED by the fact that it comprises: heating the superaustenitic stainless steel alloy up to a temperature in a working temperature range, where the superaustenitic stainless steel alloy comprises, in weight percent, based on the total weight of the alloy: up to 0.2 carbon; up to 20 manganese; 0.1 to 1.0 silicon; 14.0 to 28.0 chromium; 15.0 to 38.0 nickel; 2.0 to 9.0 molybdenum; 0.1 to 3.0 copper; 0.08 to 0.9 nitrogen; 0.1 to 5.0 tungsten; 0.5 to 5.0 cobalt; up to 1.0 titanium; up to 0.05 boron; up to 0.05 phosphorus; up to 0.05 sulfur; and iron balance and incidental impurities, and in which the working temperature range is from a solvus temperature of an intermetallic sigma phase precipitate of the superaustenitic stainless steel alloy to a temperature below an incipient melting temperature of superaustenitic stainless steel alloy; working the superaustenitic stainless steel alloy in the working temperature range; heat at least one surface region of the superaustenitic stainless steel alloy to a temperature in the working temperature range, where the temperature of the superaustenitic stainless steel alloy does not intersect a time-temperature-transformation curve for the phase precipitate intermetallic sigma of the superaustenitic stainless steel alloy over a period of time from the work of the superaustenitic stainless steel alloy until the heating of at least the surface region; keep the surface region of the superaustenitic stainless steel alloy within the working temperature range for a period of time sufficient to recreate the surface region of the superaustenitic stainless steel alloy and to minimize grain growth in the stainless steel alloy superaustenitic; and cooling the superaustenitic stainless steel alloy at a cooling rate that minimizes grain growth in the superaustenitic stainless steel alloy, where the cooling rate is in the range of 0.17 ° C per minute at 5.56 ° C per minute (0.3 degrees Fahrenheit per minute to 10 degrees Fahrenheit per minute).
[0002]
2. Method, according to claim 1, CHARACTERIZED by the fact that the step of keeping the surface region of the superaustenitic stainless steel alloy within the working temperature range for a period of time to recrystallize the region surface of the superaustenitic stainless steel alloy comprises keeping the surface region of the superaustenitic stainless steel alloy within the working temperature range for 5 minutes to 60 minutes.
[0003]
3. Method, according to claim 1, CHARACTERIZED by the fact that in the stage of working the superaustenitic stainless steel alloy the superaustenitic stainless steel alloy is worked in a temperature range from above a peak temperature from the time-temperature-transformation diagram for the precipitate of the intermetallic sigma phase of the superaustenitic stainless steel alloy to below the incipient melting temperature of the superaustenitic stainless steel alloy; and where in the step of maintaining the surface region of the superaustenitic stainless steel alloy the surface region of the superaustenitic stainless steel alloy is maintained in a temperature range from above the apex temperature of a time-temperature-transformation diagram for the precipitate of the intermetallic sigma phase of the superaustenitic stainless steel alloy to below the incipient melting temperature of the superaustenitic stainless steel alloy, where the cooling rate is in the range of 0.17 ° C per minute at 5, 56 ° C per minute (0.3 degrees Fahrenheit per minute to 10 degrees Fahrenheit per minute).
[0004]
4. Method, according to claim 3, CHARACTERIZED by the fact that in the step of maintaining the surface region of the superaustenitic stainless steel alloy the surface region of the superaustenitic stainless steel alloy is kept within a temperature range from above the apex temperature of a time-temperature-transformation diagram for the inter-metallic sigma phase precipitate of the superaustenitic stainless steel alloy to below the fledgling temperature of the superaustenitic stainless steel alloy for a sufficient time to recrystallize the surface region, transform the superaustenitic stainless steel alloy sigma phase precipitate into solution in the surface region, and minimize grain growth in the superaustenitic stainless steel alloy.
[0005]
5. Method, according to claim 3, CHARACTERIZED by the fact that in the step of maintaining the surface region of the superaustenitic stainless steel alloy the surface region of the superaustenitic stainless steel alloy is kept within a temperature range from above the peak temperature of a time-temperature-transformation diagram for the intera-metallic sigma phase precipitate of the superaustenitic stainless steel alloy to below the fledgling fuel temperature of the superaustenitic stainless steel alloy for 5 minutes at 60 minutes.
[0006]
6. Method, according to claim 3, CHARACTERIZED by the fact that in the step of cooling the superaustenitic stainless steel alloy the cooling rate is sufficient to inhibit precipitation of an intermetallic sigma precipitate in the stainless steel alloy superaustenitic.
[0007]
7. Method of processing a superaustenitic stainless steel alloy, according to claim 1, the method CHARACTERIZED by the fact that it comprises: heating the superaustenitic stainless steel alloy to a temperature in the working temperature range; keep superaustenitic stainless steel in the working temperature range long enough to dissolve a precipitate of intermetallic phase in the superaustenitic stainless steel alloy and minimize grain growth in the superaustenitic stainless steel alloy; working the superaustenitic stainless steel alloy in the working temperature range from above a peak temperature of a time-temperature-transformation curve for the intermetallic phase precipitate of the superaustenitic stainless steel alloy to below the incipient melting temperature of the superaustenitic stainless steel alloy; heat at least one surface region of the superaustenitic stainless steel alloy to a temperature in the working temperature range, where the superaustenitic stainless steel alloy does not intersect the time-temperature-transformation curve for the intermetallic phase precipitate of the superaustenitic stainless steel alloy during the period of time from the work of the alloy until heating at least the surface region of the superaustenitic stainless steel alloy; keep the surface region of the superaustenitic stainless steel alloy in the working temperature range for a sufficient retention time to recrystallize the surface region and minimize grain growth in the superaustenitic stainless steel alloy; and cooling the superaustenitic stainless steel alloy at a cooling rate that inhibits the formation of the intermetallic phase precipitate and minimizes grain growth, where the cooling rate is in the range of 0.17 ° C per minute at 5.56 ° C per minute (0.3 degrees Fahrenheit per minute to 10 degrees Fahrenheit per minute).
[0008]
8. Method, according to claim 7, CHARACTERIZED by the fact that the intermetallic precipitate phase comprises sigma phase.
[0009]
9. Method, according to claim 7, CHARACTERIZED by the fact that it also comprises the step of working the superaustenitic stainless steel alloy and the step of heating at least one surface region of the superaustenitic stainless steel alloy , transferring the superaustenitic stainless steel alloy to a heating device.
[0010]
10. Method according to any one of claims 1, 3 and 7, CHARACTERIZED by the fact that the step of working the superaustenitic stainless steel alloy comprises at least one of forging, laminating, roughing, extruding, and forming the superaustenitic stainless steel alloy.
[0011]
11. Method, according to claim 7, CHARACTERIZED by the fact that in the step of maintaining the surface region of the superaustinitic stainless steel alloy the surface region is kept within the working temperature range for 1 minute to 2 hours.
[0012]
12. Method according to claim 3 or 7, CHARACTERIZED by the fact that the step of cooling the superaustenitic stainless steel alloy comprises one of tempering, forced air cooling and air cooling of the superaustenitic stainless steel alloy.

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AU2019200606A1|2019-02-21|

JP2017501299A|2017-01-12|

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引用文献:

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

US2974076A|1954-06-10|1961-03-07|Crucible Steel Co America|Mixed phase, alpha-beta titanium alloys and method for making same|

GB847103A|1956-08-20|1960-09-07|Copperweld Steel Co|A method of making a bimetallic billet|

US3025905A|1957-02-07|1962-03-20|North American Aviation Inc|Method for precision forming|

US3015292A|1957-05-13|1962-01-02|Northrop Corp|Heated draw die|

US2932886A|1957-05-28|1960-04-19|Lukens Steel Co|Production of clad steel plates by the 2-ply method|

US2857269A|1957-07-11|1958-10-21|Crucible Steel Co America|Titanium base alloy and method of processing same|

US2893864A|1958-02-04|1959-07-07|Harris Geoffrey Thomas|Titanium base alloys|

US3060564A|1958-07-14|1962-10-30|North American Aviation Inc|Titanium forming method and means|

US3082083A|1960-12-02|1963-03-19|Armco Steel Corp|Alloy of stainless steel and articles|

US3117471A|1962-07-17|1964-01-14|Kenneth L O'connell|Method and means for making twist drills|

US3313138A|1964-03-24|1967-04-11|Crucible Steel Co America|Method of forging titanium alloy billets|

US3379522A|1966-06-20|1968-04-23|Titanium Metals Corp|Dispersoid titanium and titaniumbase alloys|

US3436277A|1966-07-08|1969-04-01|Reactive Metals Inc|Method of processing metastable beta titanium alloy|

DE1558632C3|1966-07-14|1980-08-07|Sps Technologies, Inc., Jenkintown, Pa. |Application of deformation hardening to particularly nickel-rich cobalt-nickel-chromium-molybdenum alloys|

US3489617A|1967-04-11|1970-01-13|Titanium Metals Corp|Method for refining the beta grain size of alpha and alpha-beta titanium base alloys|

US3469975A|1967-05-03|1969-09-30|Reactive Metals Inc|Method of handling crevice-corrosion inducing halide solutions|

US3605477A|1968-02-02|1971-09-20|Arne H Carlson|Precision forming of titanium alloys and the like by use of induction heating|

US4094708A|1968-02-16|1978-06-13|Imperial Metal Industries Limited|Titanium-base alloys|

US3622406A|1968-03-05|1971-11-23|Titanium Metals Corp|Dispersoid titanium and titanium-base alloys|

US3615378A|1968-10-02|1971-10-26|Reactive Metals Inc|Metastable beta titanium-base alloy|

US3584487A|1969-01-16|1971-06-15|Arne H Carlson|Precision forming of titanium alloys and the like by use of induction heating|

US3635068A|1969-05-07|1972-01-18|Iit Res Inst|Hot forming of titanium and titanium alloys|

US3649259A|1969-06-02|1972-03-14|Wyman Gordon Co|Titanium alloy|

GB1501622A|1972-02-16|1978-02-22|Int Harvester Co|Metal shaping processes|

JPS4926163B1|1970-06-17|1974-07-06|

US3676225A|1970-06-25|1972-07-11|United Aircraft Corp|Thermomechanical processing of intermediate service temperature nickel-base superalloys|

US3867208A|1970-11-24|1975-02-18|Nikolai Alexandrovich Grekov|Method for producing annular forgings|

US3686041A|1971-02-17|1972-08-22|Gen Electric|Method of producing titanium alloys having an ultrafine grain size and product produced thereby|

DE2148519A1|1971-09-29|1973-04-05|Ottensener Eisenwerk Gmbh|METHOD AND DEVICE FOR HEATING AND BOARDING RUBBES|

DE2204343C3|1972-01-31|1975-04-17|Ottensener Eisenwerk Gmbh, 2000 Hamburg|Device for heating the edge zone of a circular blank rotating around the central normal axis|

US3802877A|1972-04-18|1974-04-09|Titanium Metals Corp|High strength titanium alloys|

JPS5025418A|1973-03-02|1975-03-18|

FR2237435A5|1973-07-10|1975-02-07|Aerospatiale|

JPS5339183B2|1974-07-22|1978-10-19|

SU534518A1|1974-10-03|1976-11-05|Предприятие П/Я В-2652|The method of thermomechanical processing of alloys based on titanium|

US4098623A|1975-08-01|1978-07-04|Hitachi, Ltd.|Method for heat treatment of titanium alloy|

FR2341384B3|1976-02-23|1979-09-21|Little Inc A|

US4053330A|1976-04-19|1977-10-11|United Technologies Corporation|Method for improving fatigue properties of titanium alloy articles|

GB1479855A|1976-04-23|1977-07-13|Statni Vyzkumny Ustav Material|Protective coating for titanium alloy blades for turbine and turbo-compressor rotors|

US4121953A|1977-02-02|1978-10-24|Westinghouse Electric Corp.|High strength, austenitic, non-magnetic alloy|

US4138141A|1977-02-23|1979-02-06|General Signal Corporation|Force absorbing device and force transmission device|

US4120187A|1977-05-24|1978-10-17|General Dynamics Corporation|Forming curved segments from metal plates|

SU631234A1|1977-06-01|1978-11-05|Karpushin Viktor N|Method of straightening sheets of high-strength alloys|

US4163380A|1977-10-11|1979-08-07|Lockheed Corporation|Forming of preconsolidated metal matrix composites|

US4197643A|1978-03-14|1980-04-15|University Of Connecticut|Orthodontic appliance of titanium alloy|

US4309226A|1978-10-10|1982-01-05|Chen Charlie C|Process for preparation of near-alpha titanium alloys|

US4229216A|1979-02-22|1980-10-21|Rockwell International Corporation|Titanium base alloy|

JPS6039744B2|1979-02-23|1985-09-07|Mitsubishi Metal Corp|

US4299626A|1980-09-08|1981-11-10|Rockwell International Corporation|Titanium base alloy for superplastic forming|

CA1194346A|1981-04-17|1985-10-01|Edward F. Clatworthy|Corrosion resistant high strength nickel-base alloy|

US4639281A|1982-02-19|1987-01-27|Mcdonnell Douglas Corporation|Advanced titanium composite|

JPH0372699B2|1982-05-31|1991-11-19|Sumitomo Metal Ind|

SU1088397A1|1982-06-01|1991-02-15|Предприятие П/Я А-1186|Method of thermal straightening of articles of titanium alloys|

EP0109350B1|1982-11-10|1991-10-16|Mitsubishi Jukogyo Kabushiki Kaisha|Nickel-chromium alloy|

US4473125A|1982-11-17|1984-09-25|Fansteel Inc.|Insert for drill bits and drill stabilizers|

FR2545104B1|1983-04-26|1987-08-28|Nacam|METHOD OF LOCALIZED ANNEALING BY HEATING BY INDICATING A SHEET OF SHEET AND A HEAT TREATMENT STATION FOR IMPLEMENTING SAME|

RU1131234C|1983-06-09|1994-10-30|ВНИИ авиационных материалов|Titanium-base alloy|

US4510788A|1983-06-21|1985-04-16|Trw Inc.|Method of forging a workpiece|

SU1135798A1|1983-07-27|1985-01-23|Московский Ордена Октябрьской Революции И Ордена Трудового Красного Знамени Институт Стали И Сплавов|Method for treating billets of titanium alloys|

US4543132A|1983-10-31|1985-09-24|United Technologies Corporation|Processing for titanium alloys|

JPS6157390B2|1983-11-04|1986-12-06|Mitsubishi Metal Corp|

US4554028A|1983-12-13|1985-11-19|Carpenter Technology Corporation|Large warm worked, alloy article|

FR2557145B1|1983-12-21|1986-05-23|Snecma|THERMOMECHANICAL TREATMENT PROCESS FOR SUPERALLOYS TO OBTAIN STRUCTURES WITH HIGH MECHANICAL CHARACTERISTICS|

US4482398A|1984-01-27|1984-11-13|The United States Of America As Represented By The Secretary Of The Air Force|Method for refining microstructures of cast titanium articles|

DE3405805A1|1984-02-17|1985-08-22|Siemens AG, 1000 Berlin und 8000 München|PROTECTIVE TUBE ARRANGEMENT FOR FIBERGLASS|

US4631092A|1984-10-18|1986-12-23|The Garrett Corporation|Method for heat treating cast titanium articles to improve their mechanical properties|

GB8429892D0|1984-11-27|1985-01-03|Sonat Subsea Services Uk Ltd|Cleaning pipes|

US4690716A|1985-02-13|1987-09-01|Westinghouse Electric Corp.|Process for forming seamless tubing of zirconium or titanium alloys from welded precursors|

JPH0588304B2|1985-03-25|1993-12-21|Hitachi Metals Ltd|

AT381658B|1985-06-25|1986-11-10|Ver Edelstahlwerke Ag|METHOD FOR PRODUCING AMAGNETIC DRILL STRING PARTS|

US4668290A|1985-08-13|1987-05-26|Pfizer Hospital Products Group Inc.|Dispersion strengthened cobalt-chromium-molybdenum alloy produced by gas atomization|

US4714468A|1985-08-13|1987-12-22|Pfizer Hospital Products Group Inc.|Prosthesis formed from dispersion strengthened cobalt-chromium-molybdenum alloy produced by gas atomization|

EP0235075B1|1986-01-20|1992-05-06|Mitsubishi Jukogyo Kabushiki Kaisha|Ni-based alloy and method for preparing same|

JPH0524980B2|1986-03-28|1993-04-09|Sumitomo Metal Ind|

JPH0582453B2|1986-04-19|1993-11-19|Nippon Steel Corp|

DE3622433A1|1986-07-03|1988-01-21|Deutsche Forsch Luft Raumfahrt|METHOD FOR IMPROVING THE STATIC AND DYNAMIC MECHANICAL PROPERTIES OF + SS) TIT ALLOYS|

US4799975A|1986-10-07|1989-01-24|Nippon Kokan Kabushiki Kaisha|Method for producing beta type titanium alloy materials having excellent strength and elongation|

FR2614040B1|1987-04-16|1989-06-30|Cezus Co Europ Zirconium|PROCESS FOR THE MANUFACTURE OF A PART IN A TITANIUM ALLOY AND A PART OBTAINED|

GB8710200D0|1987-04-29|1987-06-03|Alcan Int Ltd|Light metal alloy treatment|

US4808249A|1988-05-06|1989-02-28|The United States Of America As Represented By The Secretary Of The Air Force|Method for making an integral titanium alloy article having at least two distinct microstructural regions|

US4851055A|1988-05-06|1989-07-25|The United States Of America As Represented By The Secretary Of The Air Force|Method of making titanium alloy articles having distinct microstructural regions corresponding to high creep and fatigue resistance|

US4888973A|1988-09-06|1989-12-26|Murdock, Inc.|Heater for superplastic forming of metals|

US4857269A|1988-09-09|1989-08-15|Pfizer Hospital Products Group Inc.|High strength, low modulus, ductile, biopcompatible titanium alloy|

CA2004548C|1988-12-05|1996-12-31|Kenji Aihara|Metallic material having ultra-fine grain structure and method for its manufacture|

US4957567A|1988-12-13|1990-09-18|General Electric Company|Fatigue crack growth resistant nickel-base article and alloy and method for making|

US5173134A|1988-12-14|1992-12-22|Aluminum Company Of America|Processing alpha-beta titanium alloys by beta as well as alpha plus beta forging|

US4975125A|1988-12-14|1990-12-04|Aluminum Company Of America|Titanium alpha-beta alloy fabricated material and process for preparation|

US4911884A|1989-01-30|1990-03-27|General Electric Company|High strength non-magnetic alloy|

US4980127A|1989-05-01|1990-12-25|Titanium Metals Corporation Of America |Oxidation resistant titanium-base alloy|

US4943412A|1989-05-01|1990-07-24|Timet|High strength alpha-beta titanium-base alloy|

US5366598A|1989-06-30|1994-11-22|Eltech Systems Corporation|Method of using a metal substrate of improved surface morphology|

US5256369A|1989-07-10|1993-10-26|Nkk Corporation|Titanium base alloy for excellent formability and method of making thereof and method of superplastic forming thereof|

US5074907A|1989-08-16|1991-12-24|General Electric Company|Method for developing enhanced texture in titanium alloys, and articles made thereby|

JP2822643B2|1989-08-28|1998-11-11|日本鋼管株式会社|Hot forging of sintered titanium alloy|

JP2536673B2|1989-08-29|1996-09-18|日本鋼管株式会社|Heat treatment method for titanium alloy material for cold working|

US5041262A|1989-10-06|1991-08-20|General Electric Company|Method of modifying multicomponent titanium alloys and alloy produced|

US5026520A|1989-10-23|1991-06-25|Cooper Industries, Inc.|Fine grain titanium forgings and a method for their production|

US5169597A|1989-12-21|1992-12-08|Davidson James A|Biocompatible low modulus titanium alloy for medical implants|

US5244517A|1990-03-20|1993-09-14|Daido Tokushuko Kabushiki Kaisha|Manufacturing titanium alloy component by beta forming|

US5032189A|1990-03-26|1991-07-16|The United States Of America As Represented By The Secretary Of The Air Force|Method for refining the microstructure of beta processed ingot metallurgy titanium alloy articles|

US5094812A|1990-04-12|1992-03-10|Carpenter Technology Corporation|Austenitic, non-magnetic, stainless steel alloy|

JP2841766B2|1990-07-13|1998-12-24|住友金属工業株式会社|Manufacturing method of corrosion resistant titanium alloy welded pipe|

JP2968822B2|1990-07-17|1999-11-02|株式会社神戸製鋼所|Manufacturing method of high strength and high ductility β-type Ti alloy material|

KR920004946A|1990-08-29|1992-03-28|한태희|VGA input / output port access circuit|

EP0479212B1|1990-10-01|1995-03-01|Sumitomo Metal Industries, Ltd.|Method for improving machinability of titanium and titanium alloys and free-cutting titanium alloys|

EP0484931B1|1990-11-09|1998-01-14|Kabushiki Kaisha Toyota Chuo Kenkyusho|Sintered powdered titanium alloy and method for producing the same|

RU2003417C1|1990-12-14|1993-11-30|Всероссийский институт легких сплавов|Method of making forged semifinished products of cast ti-al alloys|

FR2675818B1|1991-04-25|1993-07-16|Saint Gobain Isover|ALLOY FOR FIBERGLASS CENTRIFUGAL.|

FR2676460B1|1991-05-14|1993-07-23|Cezus Co Europ Zirconium|PROCESS FOR THE MANUFACTURE OF A TITANIUM ALLOY PIECE INCLUDING A MODIFIED HOT CORROYING AND A PIECE OBTAINED.|

US5219521A|1991-07-29|1993-06-15|Titanium Metals Corporation|Alpha-beta titanium-base alloy and method for processing thereof|

US5374323A|1991-08-26|1994-12-20|Aluminum Company Of America|Nickel base alloy forged parts|

US5360496A|1991-08-26|1994-11-01|Aluminum Company Of America|Nickel base alloy forged parts|

US5160554A|1991-08-27|1992-11-03|Titanium Metals Corporation|Alpha-beta titanium-base alloy and fastener made therefrom|

DE4228528A1|1991-08-29|1993-03-04|Okuma Machinery Works Ltd|METHOD AND DEVICE FOR METAL SHEET PROCESSING|

JP2606023B2|1991-09-02|1997-04-30|日本鋼管株式会社|Method for producing high strength and high toughness α + β type titanium alloy|

CN1028375C|1991-09-06|1995-05-10|中国科学院金属研究所|Process for producing titanium-nickel alloy foil and sheet material|

GB9121147D0|1991-10-04|1991-11-13|Ici Plc|Method for producing clad metal plate|

US5162159A|1991-11-14|1992-11-10|The Standard Oil Company|Metal alloy coated reinforcements for use in metal matrix composites|

US5201967A|1991-12-11|1993-04-13|Rmi Titanium Company|Method for improving aging response and uniformity in beta-titanium alloys|

JP3532565B2|1991-12-31|2004-05-31|ミネソタマイニングアンドマニュファクチャリングカンパニー|Removable low melt viscosity acrylic pressure sensitive adhesive|

US5226981A|1992-01-28|1993-07-13|Sandvik Special Metals, Corp.|Method of manufacturing corrosion resistant tubing from welded stock of titanium or titanium base alloy|

JP2669261B2|1992-04-23|1997-10-27|三菱電機株式会社|Forming rail manufacturing equipment|

US5399212A|1992-04-23|1995-03-21|Aluminum Company Of America|High strength titanium-aluminum alloy having improved fatigue crack growth resistance|

US5277718A|1992-06-18|1994-01-11|General Electric Company|Titanium article having improved response to ultrasonic inspection, and method therefor|

KR0148414B1|1992-07-16|1998-11-02|다나카 미노루|Titanium alloy bar suitable for producing engine valve|

JP3839493B2|1992-11-09|2006-11-01|日本発条株式会社|Method for producing member made of Ti-Al intermetallic compound|

US5310522A|1992-12-07|1994-05-10|Carondelet Foundry Company|Heat and corrosion resistant iron-nickel-chromium alloy|

US5358686A|1993-02-17|1994-10-25|Parris Warren M|Titanium alloy containing Al, V, Mo, Fe, and oxygen for plate applications|

US5332545A|1993-03-30|1994-07-26|Rmi Titanium Company|Method of making low cost Ti-6A1-4V ballistic alloy|

FR2711674B1|1993-10-21|1996-01-12|Creusot Loire|Austenitic stainless steel with high characteristics having great structural stability and uses.|

FR2712307B1|1993-11-10|1996-09-27|United Technologies Corp|Articles made of super-alloy with high mechanical and cracking resistance and their manufacturing process.|

JP3083225B2|1993-12-01|2000-09-04|オリエント時計株式会社|Manufacturing method of titanium alloy decorative article and watch exterior part|

JP2988246B2|1994-03-23|1999-12-13|日本鋼管株式会社|Method for producing type titanium alloy superplastic formed member|

ES2179940T3|1995-04-14|2003-02-01|Nippon Steel Corp|APPARATUS FOR MANUFACTURING STAINLESS STEEL BANDS.|

JP2877013B2|1994-05-25|1999-03-31|株式会社神戸製鋼所|Surface-treated metal member having excellent wear resistance and method for producing the same|

US5442847A|1994-05-31|1995-08-22|Rockwell International Corporation|Method for thermomechanical processing of ingot metallurgy near gamma titanium aluminides to refine grain size and optimize mechanical properties|

US5472526A|1994-09-30|1995-12-05|General Electric Company|Method for heat treating Ti/Al-base alloys|

AU705336B2|1994-10-14|1999-05-20|Osteonics Corp.|Low modulus, biocompatible titanium base alloys for medical devices|

US5698050A|1994-11-15|1997-12-16|Rockwell International Corporation|Method for processing-microstructure-property optimization of α-β beta titanium alloys to obtain simultaneous improvements in mechanical properties and fracture resistance|

US5759484A|1994-11-29|1998-06-02|Director General Of The Technical Research And Developent Institute, Japan Defense Agency|High strength and high ductility titanium alloy|

JP3319195B2|1994-12-05|2002-08-26|日本鋼管株式会社|Toughening method of α + β type titanium alloy|

US5547523A|1995-01-03|1996-08-20|General Electric Company|Retained strain forging of ni-base superalloys|

US6059904A|1995-04-27|2000-05-09|General Electric Company|Isothermal and high retained strain forging of Ni-base superalloys|

US5600989A|1995-06-14|1997-02-11|Segal; Vladimir|Method of and apparatus for processing tungsten heavy alloys for kinetic energy penetrators|

US6127044A|1995-09-13|2000-10-03|Kabushiki Kaisha Toshiba|Method for producing titanium alloy turbine blades and titanium alloy turbine blades|

JP3445991B2|1995-11-14|2003-09-16|Ｊｆｅスチール株式会社|Method for producing α + β type titanium alloy material having small in-plane anisotropy|

US5649280A|1996-01-02|1997-07-15|General Electric Company|Method for controlling grain size in Ni-base superalloys|

JP3873313B2|1996-01-09|2007-01-24|住友金属工業株式会社|Method for producing high-strength titanium alloy|

US5759305A|1996-02-07|1998-06-02|General Electric Company|Grain size control in nickel base superalloys|

US5861070A|1996-02-27|1999-01-19|Oregon Metallurgical Corporation|Titanium-aluminum-vanadium alloys and products made using such alloys|

JP3838445B2|1996-03-15|2006-10-25|本田技研工業株式会社|Titanium alloy brake rotor and method of manufacturing the same|

EP0834586B1|1996-03-29|2002-09-04|Kabushiki Kaisha Kobe Seiko Sho|High strength titanium alloy, product made therefrom and method for producing the same|

DE19743802C2|1996-10-07|2000-09-14|Benteler Werke Ag|Method for producing a metallic molded component|

RU2134308C1|1996-10-18|1999-08-10|Институт проблем сверхпластичности металлов РАН|Method of treatment of titanium alloys|

IT1286276B1|1996-10-24|1998-07-08|Univ Bologna|METHOD FOR THE TOTAL OR PARTIAL REMOVAL OF PESTICIDES AND / OR PHYTOPHARMACEUTICALS FROM FOOD LIQUIDS AND NOT THROUGH THE USE OF DERIVATIVES OF THE|

WO1998022629A2|1996-11-22|1998-05-28|Dongjian Li|A new class of beta titanium-based alloys with high strength and good ductility|

US5897830A|1996-12-06|1999-04-27|Dynamet Technology|P/M titanium composite casting|

US5795413A|1996-12-24|1998-08-18|General Electric Company|Dual-property alpha-beta titanium alloy forgings|

JP3959766B2|1996-12-27|2007-08-15|大同特殊鋼株式会社|Treatment method of Ti alloy with excellent heat resistance|

FR2760469B1|1997-03-05|1999-10-22|Onera |TITANIUM ALUMINUM FOR USE AT HIGH TEMPERATURES|

US5954724A|1997-03-27|1999-09-21|Davidson; James A.|Titanium molybdenum hafnium alloys for medical implants and devices|

US5980655A|1997-04-10|1999-11-09|Oremet-Wah Chang|Titanium-aluminum-vanadium alloys and products made therefrom|

US6071360A|1997-06-09|2000-06-06|The Boeing Company|Controlled strain rate forming of thick titanium plate|

US6569270B2|1997-07-11|2003-05-27|Honeywell International Inc.|Process for producing a metal article|

US6044685A|1997-08-29|2000-04-04|Wyman Gordon|Closed-die forging process and rotationally incremental forging press|

NO312446B1|1997-09-24|2002-05-13|Mitsubishi Heavy Ind Ltd|Automatic plate bending system with high frequency induction heating|

US6594355B1|1997-10-06|2003-07-15|Worldcom, Inc.|Method and apparatus for providing real time execution of specific communications services in an intelligent network|

US20050047952A1|1997-11-05|2005-03-03|Allvac Ltd.|Non-magnetic corrosion resistant high strength steels|

GB2331103A|1997-11-05|1999-05-12|Jessop Saville Limited|Non-magnetic corrosion resistant high strength steels|

FR2772790B1|1997-12-18|2000-02-04|Snecma|TITANIUM-BASED INTERMETALLIC ALLOYS OF THE Ti2AlNb TYPE WITH HIGH ELASTICITY LIMIT AND HIGH RESISTANCE TO CREEP|

EP0970764B1|1998-01-29|2009-03-18|Amino Corporation|Apparatus for dieless forming plate materials|

KR19990074014A|1998-03-05|1999-10-05|신종계|Surface processing automation device of hull shell|

EP1062374A4|1998-03-05|2004-12-22|Memry Corp|Pseudoelastic beta titanium alloy and uses therefor|

US6032508A|1998-04-24|2000-03-07|Msp Industries Corporation|Apparatus and method for near net warm forging of complex parts from axi-symmetrical workpieces|

CA2272730C|1998-05-26|2004-07-27|Kabushiki Kaisha Kobe Seiko Sho|.alpha. + .beta. type titanium alloy, a titanium alloy strip, coil-rolling process of titanium alloy, and process for producing a cold-rolled titanium alloy strip|

US20010041148A1|1998-05-26|2001-11-15|Kabushiki Kaisha Kobe Seiko Sho|Alpha + beta type titanium alloy, process for producing titanium alloy, process for coil rolling, and process for producing cold-rolled coil of titanium alloy|

US6632304B2|1998-05-28|2003-10-14|Kabushiki Kaisha Kobe Seiko Sho|Titanium alloy and production thereof|

JP3452798B2|1998-05-28|2003-09-29|株式会社神戸製鋼所|High-strength β-type Ti alloy|

JP3417844B2|1998-05-28|2003-06-16|株式会社神戸製鋼所|Manufacturing method of high-strength Ti alloy with excellent workability|

FR2779155B1|1998-05-28|2004-10-29|Kobe Steel Ltd|TITANIUM ALLOY AND ITS PREPARATION|

JP2000153372A|1998-11-19|2000-06-06|Nkk Corp|Manufacture of copper of copper alloy clad steel plate having excellent working property|

US6334912B1|1998-12-31|2002-01-01|General Electric Company|Thermomechanical method for producing superalloys with increased strength and thermal stability|

US6409852B1|1999-01-07|2002-06-25|Jiin-Huey Chern|Biocompatible low modulus titanium alloy for medical implant|

US6143241A|1999-02-09|2000-11-07|Chrysalis Technologies, Incorporated|Method of manufacturing metallic products such as sheet by cold working and flash annealing|

US6187045B1|1999-02-10|2001-02-13|Thomas K. Fehring|Enhanced biocompatible implants and alloys|

JP3681095B2|1999-02-16|2005-08-10|株式会社クボタ|Bending tube for heat exchange with internal protrusion|

JP3268639B2|1999-04-09|2002-03-25|独立行政法人産業技術総合研究所|Strong processing equipment, strong processing method and metal material to be processed|

RU2150528C1|1999-04-20|2000-06-10|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy|

US6558273B2|1999-06-08|2003-05-06|K. K. Endo Seisakusho|Method for manufacturing a golf club|

US6607693B1|1999-06-11|2003-08-19|Kabushiki Kaisha Toyota Chuo Kenkyusho|Titanium alloy and method for producing the same|

JP2001071037A|1999-09-03|2001-03-21|Matsushita Electric Ind Co Ltd|Press working method for magnesium alloy and press working device|

JP4562830B2|1999-09-10|2010-10-13|トクセン工業株式会社|Manufacturing method of β titanium alloy fine wire|

US6402859B1|1999-09-10|2002-06-11|Terumo Corporation|β-titanium alloy wire, method for its production and medical instruments made by said β-titanium alloy wire|

US7024897B2|1999-09-24|2006-04-11|Hot Metal Gas Forming Intellectual Property, Inc.|Method of forming a tubular blank into a structural component and die therefor|

RU2172359C1|1999-11-25|2001-08-20|Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов|Titanium-base alloy and product made thereof|

US6387197B1|2000-01-11|2002-05-14|General Electric Company|Titanium processing methods for ultrasonic noise reduction|

RU2156828C1|2000-02-29|2000-09-27|Воробьев Игорь Андреевич|METHOD FOR MAKING ROD TYPE ARTICLES WITH HEAD FROM DOUBLE-PHASE TITANIUM ALLOYS|

US6332935B1|2000-03-24|2001-12-25|General Electric Company|Processing of titanium-alloy billet for improved ultrasonic inspectability|

US6399215B1|2000-03-28|2002-06-04|The Regents Of The University Of California|Ultrafine-grained titanium for medical implants|

JP2001343472A|2000-03-31|2001-12-14|Seiko Epson Corp|Manufacturing method for watch outer package component, watch outer package component and watch|

JP3753608B2|2000-04-17|2006-03-08|株式会社日立製作所|Sequential molding method and apparatus|

US6532786B1|2000-04-19|2003-03-18|D-J Engineering, Inc.|Numerically controlled forming method|

US6197129B1|2000-05-04|2001-03-06|The United States Of America As Represented By The United States Department Of Energy|Method for producing ultrafine-grained materials using repetitive corrugation and straightening|

JP2001348635A|2000-06-05|2001-12-18|Nikkin Material:Kk|Titanium alloy excellent in cold workability and work hardening|

US6484387B1|2000-06-07|2002-11-26|L. H. Carbide Corporation|Progressive stamping die assembly having transversely movable die station and method of manufacturing a stack of laminae therewith|

AT408889B|2000-06-30|2002-03-25|Schoeller Bleckmann Oilfield T|CORROSION-RESISTANT MATERIAL|

RU2169782C1|2000-07-19|2001-06-27|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy and method of thermal treatment of large-size semiproducts from said alloy|

RU2169204C1|2000-07-19|2001-06-20|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy and method of thermal treatment of large-size semiproducts from said alloy|

UA40862A|2000-08-15|2001-08-15|Інститут Металофізики Національної Академії Наук України|process of thermal and mechanical treatment of high-strength beta-titanium alloys|

US6877349B2|2000-08-17|2005-04-12|Industrial Origami, Llc|Method for precision bending of sheet of materials, slit sheets fabrication process|

JP2002069591A|2000-09-01|2002-03-08|Nkk Corp|High corrosion resistant stainless steel|

UA38805A|2000-10-16|2001-05-15|Інститут Металофізики Національної Академії Наук України|alloy based on titanium|

US6946039B1|2000-11-02|2005-09-20|Honeywell International Inc.|Physical vapor deposition targets, and methods of fabricating metallic materials|

JP2002146497A|2000-11-08|2002-05-22|Daido Steel Co Ltd|METHOD FOR MANUFACTURING Ni-BASED ALLOY|

US6384388B1|2000-11-17|2002-05-07|Meritor Suspension Systems Company|Method of enhancing the bending process of a stabilizer bar|

JP3742558B2|2000-12-19|2006-02-08|新日本製鐵株式会社|Unidirectionally rolled titanium plate with high ductility and small in-plane material anisotropy and method for producing the same|

EP1382695A4|2001-02-28|2004-08-11|Jfe Steel Corp|Titanium alloy bar and method for production thereof|

EP1375690B1|2001-03-26|2006-03-15|Kabushiki Kaisha Toyota Chuo Kenkyusho|High strength titanium alloy and method for production thereof|

US6539765B2|2001-03-28|2003-04-01|Gary Gates|Rotary forging and quenching apparatus and method|

US6536110B2|2001-04-17|2003-03-25|United Technologies Corporation|Integrally bladed rotor airfoil fabrication and repair techniques|

US6576068B2|2001-04-24|2003-06-10|Ati Properties, Inc.|Method of producing stainless steels having improved corrosion resistance|

JP4031992B2|2001-04-27|2008-01-09|リサーチインスティチュートオブインダストリアルサイエンスアンドテクノロジー|High manganese duplex stainless steel with excellent hot workability and method for producing the same|

RU2203974C2|2001-05-07|2003-05-10|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy|

DE10128199B4|2001-06-11|2007-07-12|Benteler Automobiltechnik Gmbh|Device for forming metal sheets|

RU2197555C1|2001-07-11|2003-01-27|Общество с ограниченной ответственностью Научно-производственное предприятие "Велес"|Method of manufacturing rod parts with heads from titanium alloys|

JP3934372B2|2001-08-15|2007-06-20|株式会社神戸製鋼所|High strength and low Young's modulus β-type Ti alloy and method for producing the same|

JP2003074566A|2001-08-31|2003-03-12|Nsk Ltd|Rolling device|

CN1159472C|2001-09-04|2004-07-28|北京航空材料研究院|Titanium alloy quasi-beta forging process|

JP4019668B2|2001-09-05|2007-12-12|Ｊｆｅスチール株式会社|High toughness titanium alloy material and manufacturing method thereof|

SE525252C2|2001-11-22|2005-01-11|Sandvik Ab|Super austenitic stainless steel and the use of this steel|

US6663501B2|2001-12-07|2003-12-16|Charlie C. Chen|Macro-fiber process for manufacturing a face for a metal wood golf club|

CN1602369A|2001-12-14|2005-03-30|Ati资产公司|Method for processing beta titanium alloys|

JP3777130B2|2002-02-19|2006-05-24|本田技研工業株式会社|Sequential molding equipment|

FR2836640B1|2002-03-01|2004-09-10|Snecma Moteurs|THIN PRODUCTS OF TITANIUM BETA OR QUASI BETA ALLOYS MANUFACTURING BY FORGING|

JP2003285126A|2002-03-25|2003-10-07|Toyota Motor Corp|Warm plastic working method|

RU2217260C1|2002-04-04|2003-11-27|ОАО Верхнесалдинское металлургическое производственное объединение|METHOD FOR MAKING INTERMEDIATE BLANKS OF α AND α TITANIUM ALLOYS|

US6786985B2|2002-05-09|2004-09-07|Titanium Metals Corp.|Alpha-beta Ti-Ai-V-Mo-Fe alloy|

JP2003334633A|2002-05-16|2003-11-25|Daido Steel Co Ltd|Manufacturing method for stepped shaft-like article|

US7410610B2|2002-06-14|2008-08-12|General Electric Company|Method for producing a titanium metallic composition having titanium boride particles dispersed therein|

US6918974B2|2002-08-26|2005-07-19|General Electric Company|Processing of alpha-beta titanium alloy workpieces for good ultrasonic inspectability|

JP4257581B2|2002-09-20|2009-04-22|株式会社豊田中央研究所|Titanium alloy and manufacturing method thereof|

AU2003299073A1|2002-09-30|2004-04-19|Zenji Horita|Method of working metal, metal body obtained by the method and metal-containing ceramic body obtained by the method|

JP2004131761A|2002-10-08|2004-04-30|Jfe Steel Kk|Method for producing fastener material made of titanium alloy|

US6932877B2|2002-10-31|2005-08-23|General Electric Company|Quasi-isothermal forging of a nickel-base superalloy|

FI115830B|2002-11-01|2005-07-29|Metso Powdermet Oy|Process for the manufacture of multi-material components and multi-material components|

US7008491B2|2002-11-12|2006-03-07|General Electric Company|Method for fabricating an article of an alpha-beta titanium alloy by forging|

AU2003295609A1|2002-11-15|2004-06-15|University Of Utah|Integral titanium boride coatings on titanium surfaces and associated methods|

US20040099350A1|2002-11-21|2004-05-27|Mantione John V.|Titanium alloys, methods of forming the same, and articles formed therefrom|

RU2321674C2|2002-12-26|2008-04-10|Дженерал Электрик Компани|Method for producing homogenous fine-grain titanium material |

US7010950B2|2003-01-17|2006-03-14|Visteon Global Technologies, Inc.|Suspension component having localized material strengthening|

JP4424471B2|2003-01-29|2010-03-03|住友金属工業株式会社|Austenitic stainless steel and method for producing the same|

DE10303458A1|2003-01-29|2004-08-19|Amino Corp., Fujinomiya|Shaping method for thin metal sheet, involves finishing rough forming body to product shape using tool that moves three-dimensionally with mold punch as mold surface sandwiching sheet thickness while mold punch is kept under pushed state|

RU2234998C1|2003-01-30|2004-08-27|Антонов Александр Игоревич|Method for making hollow cylindrical elongated blank |

WO2004083477A1|2003-03-20|2004-09-30|Sumitomo Metal Industries, Ltd.|High-strength stainless steel, container and hardware made of such steel|

JP4209233B2|2003-03-28|2009-01-14|株式会社日立製作所|Sequential molding machine|

JP3838216B2|2003-04-25|2006-10-25|住友金属工業株式会社|Austenitic stainless steel|

US20040221929A1|2003-05-09|2004-11-11|Hebda John J.|Processing of titanium-aluminum-vanadium alloys and products made thereby|

JP4041774B2|2003-06-05|2008-01-30|住友金属工業株式会社|Method for producing β-type titanium alloy material|

US7785429B2|2003-06-10|2010-08-31|The Boeing Company|Tough, high-strength titanium alloys; methods of heat treating titanium alloys|

US7073559B2|2003-07-02|2006-07-11|Ati Properties, Inc.|Method for producing metal fibers|

CA2535038C|2003-08-05|2012-09-25|Dynamet Holdings, Inc.|Process for manufacture of fasteners from titanium or a titanium alloy|

AT412727B|2003-12-03|2005-06-27|Boehler Edelstahl|CORROSION RESISTANT, AUSTENITIC STEEL ALLOY|

US8128764B2|2003-12-11|2012-03-06|Miracle Daniel B|Titanium alloy microstructural refinement method and high temperature, high strain rate superplastic forming of titanium alloys|

US7038426B2|2003-12-16|2006-05-02|The Boeing Company|Method for prolonging the life of lithium ion batteries|

US20050145310A1|2003-12-24|2005-07-07|General Electric Company|Method for producing homogeneous fine grain titanium materials suitable for ultrasonic inspection|

JP2005281855A|2004-03-04|2005-10-13|Daido Steel Co Ltd|Heat-resistant austenitic stainless steel and production process thereof|

US7837812B2|2004-05-21|2010-11-23|Ati Properties, Inc.|Metastable beta-titanium alloys and methods of processing the same by direct aging|

RU2256713C1|2004-06-18|2005-07-20|Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" |Titanium-base alloy and article made of thereof|

US7449075B2|2004-06-28|2008-11-11|General Electric Company|Method for producing a beta-processed alpha-beta titanium-alloy article|

RU2269584C1|2004-07-30|2006-02-10|Открытое Акционерное Общество "Корпорация Всмпо-Ависма"|Titanium-base alloy|

US20060045789A1|2004-09-02|2006-03-02|Coastcast Corporation|High strength low cost titanium and method for making same|

US7096596B2|2004-09-21|2006-08-29|Alltrade Tools Llc|Tape measure device|

US7601232B2|2004-10-01|2009-10-13|Dynamic Flowform Corp.|α-β titanium alloy tubes and methods of flowforming the same|

SE528008C2|2004-12-28|2006-08-01|Outokumpu Stainless Ab|Austenitic stainless steel and steel product|

US7360387B2|2005-01-31|2008-04-22|Showa Denko K.K.|Upsetting method and upsetting apparatus|

US20060243356A1|2005-02-02|2006-11-02|Yuusuke Oikawa|Austenite-type stainless steel hot-rolling steel material with excellent corrosion resistance, proof-stress, and low-temperature toughness and production method thereof|

JP5208354B2|2005-04-11|2013-06-12|新日鐵住金株式会社|Austenitic stainless steel|

RU2288967C1|2005-04-15|2006-12-10|Закрытое акционерное общество ПКФ "Проммет-спецсталь"|Corrosion-resisting alloy and article made of its|

US7984635B2|2005-04-22|2011-07-26|K.U. Leuven Research & Development|Asymmetric incremental sheet forming system|

RU2283889C1|2005-05-16|2006-09-20|ОАО "Корпорация ВСМПО-АВИСМА"|Titanium base alloy|

JP4787548B2|2005-06-07|2011-10-05|株式会社アミノ|Thin plate forming method and apparatus|

DE102005027259B4|2005-06-13|2012-09-27|Daimler Ag|Process for the production of metallic components by semi-hot forming|

US20070009858A1|2005-06-23|2007-01-11|Hatton John F|Dental repair material|

KR100677465B1|2005-08-10|2007-02-07|이영화|Linear Induction Heating Coil Tool for Plate Bending|

US7531054B2|2005-08-24|2009-05-12|Ati Properties, Inc.|Nickel alloy and method including direct aging|

US8337750B2|2005-09-13|2012-12-25|Ati Properties, Inc.|Titanium alloys including increased oxygen content and exhibiting improved mechanical properties|

US7590481B2|2005-09-19|2009-09-15|Ford Global Technologies, Llc|Integrated vehicle control system using dynamically determined vehicle conditions|

JP4915202B2|2005-11-03|2012-04-11|大同特殊鋼株式会社|High nitrogen austenitic stainless steel|

US7669452B2|2005-11-04|2010-03-02|Cyril Bath Company|Titanium stretch forming apparatus and method|

JP2009521660A|2005-12-21|2009-06-04|エクソンモービルリサーチアンドエンジニアリングカンパニー|Corrosion resistant material for suppressing fouling, heat transfer device having improved corrosion resistance and fouling resistance, and method for suppressing fouling|

US7611592B2|2006-02-23|2009-11-03|Ati Properties, Inc.|Methods of beta processing titanium alloys|

JP5050199B2|2006-03-30|2012-10-17|国立大学法人電気通信大学|Magnesium alloy material manufacturing method and apparatus, and magnesium alloy material|

US20090165903A1|2006-04-03|2009-07-02|Hiromi Miura|Material Having Ultrafine Grained Structure and Method of Fabricating Thereof|

KR100740715B1|2006-06-02|2007-07-18|경상대학교산학협력단|Ti-ni alloy-ni sulfide element for combined current collector-electrode|

US7879286B2|2006-06-07|2011-02-01|Miracle Daniel B|Method of producing high strength, high stiffness and high ductility titanium alloys|

JP5187713B2|2006-06-09|2013-04-24|国立大学法人電気通信大学|Metal material refinement processing method|

US20080000554A1|2006-06-23|2008-01-03|Jorgensen Forge Corporation|Austenitic paramagnetic corrosion resistant material|

WO2008017257A1|2006-08-02|2008-02-14|Hangzhou Huitong Driving Chain Co., Ltd.|A bended link plate and the method to making thereof|

US20080103543A1|2006-10-31|2008-05-01|Medtronic, Inc.|Implantable medical device with titanium alloy housing|

CN101202528B|2006-12-11|2012-10-10|丹佛斯传动有限公司|Electronic device and electric motor frequency converter|

JP2008200730A|2007-02-21|2008-09-04|Daido Steel Co Ltd|METHOD FOR MANUFACTURING Ni-BASED HEAT-RESISTANT ALLOY|

CN101294264A|2007-04-24|2008-10-29|宝山钢铁股份有限公司|Process for manufacturing type alpha+beta titanium alloy rod bar for rotor impeller vane|

US20080300552A1|2007-06-01|2008-12-04|Cichocki Frank R|Thermal forming of refractory alloy surgical needles|

CN100567534C|2007-06-19|2009-12-09|中国科学院金属研究所|The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method|

US20090000706A1|2007-06-28|2009-01-01|General Electric Company|Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys|

DE102007039998B4|2007-08-23|2014-05-22|Benteler Defense Gmbh & Co. Kg|Armor for a vehicle|

RU2364660C1|2007-11-26|2009-08-20|Владимир Валентинович Латыш|Method of manufacturing ufg sections from titanium alloys|

JP2009138218A|2007-12-05|2009-06-25|Nissan Motor Co Ltd|Titanium alloy member and method for manufacturing titanium alloy member|

CN100547105C|2007-12-10|2009-10-07|巨龙钢管有限公司|A kind of X80 steel bend pipe and bending technique thereof|

RU2461641C2|2007-12-20|2012-09-20|ЭйТиАй ПРОПЕРТИЗ, ИНК.|Austenitic stainless steel with low content of nickel and including stabilising elements|

KR100977801B1|2007-12-26|2010-08-25|주식회사 포스코|Titanium alloy with exellent hardness and ductility and method thereof|

JP2009167502A|2008-01-18|2009-07-30|Daido Steel Co Ltd|Austenitic stainless steel for fuel cell separator|

US8075714B2|2008-01-22|2011-12-13|Caterpillar Inc.|Localized induction heating for residual stress optimization|

RU2368695C1|2008-01-30|2009-09-27|Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" |Method of product's receiving made of high-alloy heat-resistant nickel alloy|

RU2382686C2|2008-02-12|2010-02-27|Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет"|Method of punching of blanks from nanostructured titanium alloys|

DE102008014559A1|2008-03-15|2009-09-17|Elringklinger Ag|Process for partially forming a sheet metal layer of a flat gasket produced from a spring steel sheet and device for carrying out this process|

JP4433230B2|2008-05-22|2010-03-17|住友金属工業株式会社|High-strength Ni-base alloy tube for nuclear power and its manufacturing method|

JP2009299110A|2008-06-11|2009-12-24|Kobe Steel Ltd|HIGH-STRENGTH alpha-beta TYPE TITANIUM ALLOY SUPERIOR IN INTERMITTENT MACHINABILITY|

JP5299610B2|2008-06-12|2013-09-25|大同特殊鋼株式会社|Method for producing Ni-Cr-Fe ternary alloy material|

US8226568B2|2008-07-15|2012-07-24|Nellcor Puritan Bennett Llc|Signal processing systems and methods using basis functions and wavelet transforms|

RU2392348C2|2008-08-20|2010-06-20|Федеральное Государственное Унитарное Предприятие "Центральный Научно-Исследовательский Институт Конструкционных Материалов "Прометей" |Corrosion-proof high-strength non-magnetic steel and method of thermal deformation processing of such steel|

JP5315888B2|2008-09-22|2013-10-16|Ｊｆｅスチール株式会社|α-β type titanium alloy and method for melting the same|

CN101684530A|2008-09-28|2010-03-31|杭正奎|Ultra high-temperature resistant nickel-chrome alloy and manufacturing method thereof|

RU2378410C1|2008-10-01|2010-01-10|Открытое акционерное общество "Корпорация ВСПМО-АВИСМА"|Manufacturing method of plates from duplex titanium alloys|

US8408039B2|2008-10-07|2013-04-02|Northwestern University|Microforming method and apparatus|

RU2383654C1|2008-10-22|2010-03-10|Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет"|Nano-structural technically pure titanium for bio-medicine and method of producing wire out of it|

US8430075B2|2008-12-16|2013-04-30|L.E. Jones Company|Superaustenitic stainless steel and method of making and use thereof|

RU2393936C1|2009-03-25|2010-07-10|Владимир Алексеевич Шундалов|Method of producing ultra-fine-grain billets from metals and alloys|

US8578748B2|2009-04-08|2013-11-12|The Boeing Company|Reducing force needed to form a shape from a sheet metal|

US8316687B2|2009-08-12|2012-11-27|The Boeing Company|Method for making a tool used to manufacture composite parts|

CN101637789B|2009-08-18|2011-06-08|西安航天博诚新材料有限公司|Resistance heat tension straightening device and straightening method thereof|

RU2413030C1|2009-10-22|2011-02-27|Федеральное Государственное Унитарное Предприятие "Центральный научно-исследовательский институт черной металлургии им. И.П. Бардина" |Tube stock out of corrosion resistant steel|

JP2011121118A|2009-11-11|2011-06-23|Univ Of Electro-Communications|Method and equipment for multidirectional forging of difficult-to-work metallic material, and metallic material|

WO2011062231A1|2009-11-19|2011-05-26|独立行政法人物質・材料研究機構|Heat-resistant superalloy|

KR20110069602A|2009-12-17|2011-06-23|주식회사 포스코|A method of manufacturing ostenite-origin stainless steel plate by using twin roll strip caster and austenite stainless steel plate manufactured thereby|

RU2425164C1|2010-01-20|2011-07-27|Открытое Акционерное Общество "Корпорация Всмпо-Ависма"|Secondary titanium alloy and procedure for its fabrication|

US10053758B2|2010-01-22|2018-08-21|Ati Properties Llc|Production of high strength titanium|

DE102010009185A1|2010-02-24|2011-11-17|Benteler Automobiltechnik Gmbh|Sheet metal component is made of steel armor and is formed as profile component with bend, where profile component is manufactured from armored steel plate by hot forming in single-piece manner|

CN102933331B|2010-05-17|2015-08-26|麦格纳国际公司|For the method and apparatus formed the material with low ductility|

CA2706215C|2010-05-31|2017-07-04|Corrosion Service Company Limited|Method and apparatus for providing electrochemical corrosion protection|

US10207312B2|2010-06-14|2019-02-19|Ati Properties Llc|Lubrication processes for enhanced forgeability|

US9255316B2|2010-07-19|2016-02-09|Ati Properties, Inc.|Processing of α+β titanium alloys|

US8499605B2|2010-07-28|2013-08-06|Ati Properties, Inc.|Hot stretch straightening of high strength α/β processed titanium|

US8613818B2|2010-09-15|2013-12-24|Ati Properties, Inc.|Processing routes for titanium and titanium alloys|

US9206497B2|2010-09-15|2015-12-08|Ati Properties, Inc.|Methods for processing titanium alloys|

US20120067100A1|2010-09-20|2012-03-22|Ati Properties, Inc.|Elevated Temperature Forming Methods for Metallic Materials|

US10513755B2|2010-09-23|2019-12-24|Ati Properties Llc|High strength alpha/beta titanium alloy fasteners and fastener stock|

US20120076686A1|2010-09-23|2012-03-29|Ati Properties, Inc.|High strength alpha/beta titanium alloy|

US20120076611A1|2010-09-23|2012-03-29|Ati Properties, Inc.|High Strength Alpha/Beta Titanium Alloy Fasteners and Fastener Stock|

RU2447185C1|2010-10-18|2012-04-10|Владимир Дмитриевич Горбач|High-strength nonmagnetic rustproof casting steel and method of its thermal treatment|

RU2441089C1|2010-12-30|2012-01-27|Юрий Васильевич Кузнецов|ANTIRUST ALLOY BASED ON Fe-Cr-Ni, ARTICLE THEREFROM AND METHOD OF PRODUCING SAID ARTICLE|

JP2012140690A|2011-01-06|2012-07-26|Sanyo Special Steel Co Ltd|Method of manufacturing two-phase stainless steel excellent in toughness and corrosion resistance|

JP5733857B2|2011-02-28|2015-06-10|国立研究開発法人物質・材料研究機構|Non-magnetic high-strength molded article and its manufacturing method|

CN103492099B|2011-04-25|2015-09-09|日立金属株式会社|The manufacture method of ladder forged material|

US9732408B2|2011-04-29|2017-08-15|Aktiebolaget Skf|Heat-treatment of an alloy for a bearing component|

US8679269B2|2011-05-05|2014-03-25|General Electric Company|Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby|

CN102212716B|2011-05-06|2013-03-27|中国航空工业集团公司北京航空材料研究院|Low-cost alpha and beta-type titanium alloy|

US8652400B2|2011-06-01|2014-02-18|Ati Properties, Inc.|Thermo-mechanical processing of nickel-base alloys|

US9034247B2|2011-06-09|2015-05-19|General Electric Company|Alumina-forming cobalt-nickel base alloy and method of making an article therefrom|

ES2620310T3|2011-06-17|2017-06-28|Titanium Metals Corporation|Method for manufacturing alpha-beta alloy plates from Ti-Al-V-Mo-Fe|

US20130133793A1|2011-11-30|2013-05-30|Ati Properties, Inc.|Nickel-base alloy heat treatments, nickel-base alloys, and articles including nickel-base alloys|

US9347121B2|2011-12-20|2016-05-24|Ati Properties, Inc.|High strength, corrosion resistant austenitic alloys|

US9869003B2|2013-02-26|2018-01-16|Ati Properties Llc|Methods for processing alloys|

US9192981B2|2013-03-11|2015-11-24|Ati Properties, Inc.|Thermomechanical processing of high strength non-magnetic corrosion resistant material|

US9777361B2|2013-03-15|2017-10-03|Ati Properties Llc|Thermomechanical processing of alpha-beta titanium alloys|

US9050647B2|2013-03-15|2015-06-09|Ati Properties, Inc.|Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys|

JP6171762B2|2013-09-10|2017-08-02|大同特殊鋼株式会社|Method of forging Ni-base heat-resistant alloy|

US10094003B2|2015-01-12|2018-10-09|Ati Properties Llc|Titanium alloy|

US10502252B2|2015-11-23|2019-12-10|Ati Properties Llc|Processing of alpha-beta titanium alloys|US20040221929A1|2003-05-09|2004-11-11|Hebda John J.|Processing of titanium-aluminum-vanadium alloys and products made thereby|

US7837812B2|2004-05-21|2010-11-23|Ati Properties, Inc.|Metastable beta-titanium alloys and methods of processing the same by direct aging|

US10053758B2|2010-01-22|2018-08-21|Ati Properties Llc|Production of high strength titanium|

US9255316B2|2010-07-19|2016-02-09|Ati Properties, Inc.|Processing of α+β titanium alloys|

US9206497B2|2010-09-15|2015-12-08|Ati Properties, Inc.|Methods for processing titanium alloys|

US8613818B2|2010-09-15|2013-12-24|Ati Properties, Inc.|Processing routes for titanium and titanium alloys|

US10513755B2|2010-09-23|2019-12-24|Ati Properties Llc|High strength alpha/beta titanium alloy fasteners and fastener stock|

US8652400B2|2011-06-01|2014-02-18|Ati Properties, Inc.|Thermo-mechanical processing of nickel-base alloys|

US20160194753A1|2012-12-27|2016-07-07|Showa Denko K.K.|SiC-FILM FORMATION DEVICE AND METHOD FOR PRODUCING SiC FILM|

WO2014103728A1|2012-12-27|2014-07-03|昭和電工株式会社|Film-forming device|

US9869003B2|2013-02-26|2018-01-16|Ati Properties Llc|Methods for processing alloys|

US9192981B2|2013-03-11|2015-11-24|Ati Properties, Inc.|Thermomechanical processing of high strength non-magnetic corrosion resistant material|

US9777361B2|2013-03-15|2017-10-03|Ati Properties Llc|Thermomechanical processing of alpha-beta titanium alloys|

US10094003B2|2015-01-12|2018-10-09|Ati Properties Llc|Titanium alloy|

US9902641B2|2015-03-20|2018-02-27|Corning Incorporated|Molds for shaping glass-based materials and methods for making the same|

US10502252B2|2015-11-23|2019-12-10|Ati Properties Llc|Processing of alpha-beta titanium alloys|

KR20180095868A|2015-12-14|2018-08-28|스와겔로크 컴패니|High alloy stainless steel forgings manufactured without solution annealing|

CA3008504A1|2015-12-22|2017-06-29|Ecole De Technologie Superieure|A method for heat treating by induction an alloy component for generating microstructure gradients and an alloy component heat treated according to the method|

CN106282729B|2016-08-31|2018-01-16|彭书成|A kind of superalloy and preparation method thereof|

CN106636951A|2016-11-10|2017-05-10|合肥辰泰安全设备有限责任公司|Alloy material for spraying nozzle|

US20190136335A1|2017-11-07|2019-05-09|Swagelok Company|Highly alloyed stainless steel forgings made without solution anneal|

CN111041395B|2018-10-12|2021-07-06|南京理工大学|Ultra-high density twin crystal titanium and preparation method thereof|

CN109454122B|2018-11-19|2020-03-31|深圳市业展电子有限公司|Preparation process of nickel-chromium-aluminum-iron precision resistance alloy strip|

KR102023447B1|2019-04-09|2019-09-24|정태석|Food tank with sample gathering structure for inspecting and measuring|

CN110066957A|2019-05-17|2019-07-30|国家电投集团科学技术研究院有限公司|Corrosion-resistant super austenitic stainless steel of modified and preparation method thereof|

CN110487832A|2019-08-29|2019-11-22|西安理工大学|A kind of single crystal super alloy blast recrystallizes the evaluation method of tendency in the process|

RU2752819C1|2020-12-02|2021-08-06|Акционерное общество "Металлургический завод "Электросталь"|Method for production of rods with diameter of less than 60 mm from heat-resistant nickel-based alloy vzh175-vi by hot extrusion|

CN112775436A|2020-12-22|2021-05-11|西安交通大学|Manufacturing method for promoting titanium alloy additive manufacturing process to generate isometric crystals|

法律状态:
2017-10-03| B25D| Requested change of name of applicant approved|Owner name: ATI PROPERTIES LLC (US) |

2019-07-30| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|

2020-09-08| B07A| Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]|

2021-01-05| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

2021-03-09| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 28/10/2014, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

申请号 | 申请日 | 专利标题

US14/077,699|US11111552B2|2013-11-12|2013-11-12|Methods for processing metal alloys|

US14/077,699|2013-11-12|

PCT/US2014/062525|WO2015073201A1|2013-11-12|2014-10-28|Methods for processing metal alloys|

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