• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Created are nickel-base superalloys comprising: about 7.0 weight percent (wt%) to 12.0 wt% chromium, about 0.1 wt% to 5 wt% molybdenum, about 0.2 wt%. % to 4.5% by weight of titanium, about 4% by weight to 6% by weight of aluminum, about 3% by weight to 4.9% by weight of cobalt, about 6.0% by weight to about 9.0 wt% tungsten, about 4.0 wt% to 6.5 wt% tantalum, about 0.05 wt% to 0.6 wt% hafnium, to about 1, 0 wt% niobium, to about 0.02 wt% boron, and up to about 0.1 wt% carbon, with nickel and incidental impurities forming the difference to 100%. The alloys may be cast, directionally solidified, and heat treated to produce articles having a γ 'content of greater than about 50%.
    公开号:CH701641B1
    申请号:CH01366/10
    申请日:2010-08-25
    公开日:2016-06-15
    发明作者:Hanlon Timothy；Didomizio Richard；Francis Henry Michael；Suzuki Akane；Samuel Peck Arthur；Joseph Balsone Stephen
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    The present description relates to nickel-based alloys and articles based thereon.
    Gas turbine engines operate in extreme environmental conditions, with engine components, in particular those which are arranged in the turbine section, are exposed to high operating temperatures and stresses. Power turbine blades (or blades), particularly those that may be up to about 91.44 cm (36 inches) or more in length and weight up to about 18.14 kg (40 pounds) or more, require a balance of Properties which include, but are not limited to, mold cracking resistance, tensile strength, ductility, creep resistance, corrosion resistance, heat corrosion resistance, low staining, sufficiently low density, reasonable cost, and a reasonably large heat treatment window.
    Superalloys have heretofore been used in these demanding applications because of their ability to maintain relatively high strengths to about 75% of their respective melting points, while additionally exhibiting excellent environmental resistance. Nickel base superalloys in particular have been used extensively in all parts of gas turbine engines, e.g. in turbine blade, nozzle and jacket applications. However, conventional nickel-base superalloys used in last stage blade applications may be difficult to cast, resulting in low yields. The constantly increasing demands on the gas turbine combustion temperature in these applications were limited in the past to an improvement in the mechanical and environmental influences of the material properties.
    Directional solidification has been used successfully to optimize creep and tear behavior in nickel-based superalloy blade applications. A preferred alignment of grains in the direction of the main stress axis, which essentially coincides with the longitudinal direction, produces a columnar grain structure which eliminates grain boundaries running transversely to the direction of growth. Such an alignment also enables a favorable modulus of elasticity in the longitudinal direction, which is advantageous for the material fatigue properties of the component.
    Compared to conventionally cast alloy articles, the use of the directional solidification process produces articles with substantial improvements in strength, ductility, and resistance to thermal fatigue. However, due to the presence of columnar grain boundaries, reduced strength and ductility properties in the transverse direction can still be found in such articles. In an effort to improve the transverse grain boundary strength of such articles, additional alloying elements, e.g. Hafnium, carbon, boron and zirconium are used. However, the addition of these and other elements can lead to a deterioration in other desired properties, e.g. the melting temperature, and it has therefore hitherto been necessary to make a compromise for this with a view to a balance of properties.
    Thus, there remains a need for nickel-based alloys that have other or substantially all of the desirable properties for use in gas turbine engines, e.g. Corrosion resistance, oxidation, creep and high temperature resistance. Further, it would be desirable if alloys produced in this way either do not contain elements which are substantially detrimental to the desired properties or are processed in a suitable manner so that any deterioration in the desired properties is minimized or eliminated.
    Brief description of the invention
    According to the invention, nickel-based alloys are created which have: about 7.0% by weight (% by weight) to about 12.0% by weight of chromium, about 0.1% by weight to about 5% by weight % Molybdenum, about 0.2% to about 4.5% by weight titanium, about 4% to about 6% by weight aluminum, about 3% by weight to about 4.9% Wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 wt% -% to about 0.6% by weight hafnium, up to about 1.0% by weight niobium, up to about 0.02% by weight boron, and up to about 0.1% by weight carbon, with nickel and random impurities make the difference to 100%.
    Furthermore, according to a particular embodiment of the invention, nickel-based alloys are created which have: about 9.0% by weight to about 11.0% by weight chromium, about 0.5% by weight to about 3.0% by weight % Molybdenum, about 0.5 wt% to about 3.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3.5 wt% to about 4 , 25 wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 Wt% to about 0.5 wt% hafnium, up to about 1.0 wt% niobium, up to about 0.01 wt% boron, and up to about 0.07 wt% carbon, wherein Nickel and incidental impurities make up 100% of the difference.
    In addition, the invention relates to a cast article made of a nickel-based alloy, which has: about 7.0 wt .-% (wt .-%) to about 12.0 wt .-% chromium, about 0.1 wt .-% to about 5 wt% molybdenum, about 0.2 wt% to about 4.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3 wt% to about 4.9 wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0 0.05 wt% to about 0.6 wt% hafnium, up to about 1.0 wt% niobium, up to about 0.02 wt% boron, and up to about 0.1 wt% carbon where nickel and incidental impurities make up 100% of the difference. The cast article has a γ'-share of more than about 50%.
    Furthermore, according to a particular embodiment of the invention, a cast article is created which is formed using a nickel-based alloy which has: about 9.0% by weight to about 11.0% by weight chromium, about 0.5% by weight. -% to about 3.0% by weight molybdenum, about 0.5% by weight to about 3.5% by weight titanium, about 4% by weight to about 6% by weight aluminum, about 3, 5 wt% to about 4.25 wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt%. -% tantalum, about 0.05% by weight to about 0.5% by weight hafnium, up to about 1.0% by weight niobium, up to about 0.01% by weight boron, and up to about 0, 07% by weight carbon, with nickel and incidental impurities making up the difference to 100%. The cast article has a γ'-share of more than about 50%.
    The invention also relates to a method of making a cast and heat treated article. The method includes providing a nickel-based alloy comprising: about 7.0 wt% (wt%) to about 12.0 wt% chromium, about 0.1 wt% to about 5 wt% % Molybdenum, about 0.2% by weight to about 4.5% by weight titanium, about 4% by weight to about 6% by weight aluminum, about 3% by weight to about 4.9% by weight. -% cobalt, about 6.0% by weight to about 9.0% by weight tungsten, about 4.0% by weight to about 6.5% by weight tantalum, about 0.05% by weight up to about 0.6 wt% hafnium, up to about 1.0 wt% niobium, up to about 0.02 wt% boron, and up to about 0.1 wt% carbon, with nickel and incidental impurities make the difference to 100%. The alloy is melted and directionally solidified to create the article and the article is heat treated so that the article has a γ 'content greater than about 50%.
    In an additional embodiment, a method of making a molded and heat treated article is provided. The method includes providing a nickel-based alloy comprising: about 9.0 wt% to about 11.0 wt% chromium, about 0.5 wt% to about 3.0 wt% molybdenum, about 0.5 wt% to about 3.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3.5 wt% to about 4.25 wt% Cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 wt% to about 0.5 wt% hafnium, up to about 1.0 wt% niobium, up to about 0.01 wt% boron, and up to about 0.07 wt% carbon, with nickel and incidental impurities being the difference 100% make up. The alloy is melted and directionally solidified to create the article and the article is heat treated so that the article has a γ 'content greater than about 50%.
    Detailed description of the invention
    Unless otherwise defined, the meaning of the technical and scientific terms used herein is consistent with the meaning commonly understood by those skilled in the art in the field of this invention. As used herein, the terms "first", "second" and the like do not define any order, quantity, or ranking, but rather serve to distinguish one element from another. Furthermore, the indefinite article “a” or “an” does not denote a restriction on the quantity, but rather means that at least one relevant element is present, and the terms “front”, “rear”, “bottom” and / or “top” are used, unless otherwise noted, for the purpose of simplifying the description and are not limited to any position or spatial orientation. If ranges are disclosed, the endpoints of all ranges relating to the same component or property are included and can be combined independently of one another (e.g. include ranges of up to about 25% by weight, or more specifically about 5% by weight to about 20% by weight) % ”Includes the endpoints and all intermediate values of the ranges from“ about 5% by weight to about 25% by weight ”, etc.). The modifying term “about” used in connection with a quantity includes the stated value and includes the meaning given by the context (it includes e.g. the error deviation that may exist in connection with a measurement of the specific quantity).
    A nickel base superalloy is provided herein which has a unique combination of alloying elements which make the alloy particularly suitable for casting and directional solidification to produce articles, e.g. Gas turbine blades that have a combination of improved mechanical properties and increased resistance to oxidation and heat corrosion. More specifically, components formed on the basis of the superalloys described can have improved casting crack resistance and a larger heat treatment window compared to conventional nickel-based superalloys, so that manufacturing costs can be reduced and the yield of castings can be increased. In addition, articles made using the present superalloys can also have increased strength, ductility and creep resistance compared to conventional nickel-based superalloys so that the articles can be used at higher operating temperatures and / or have a longer useful life and / or in the Example of turbine blades can be made longer in order to achieve improved efficiency.
    It is well known that alloying elements tend to partition between the phases of an alloy in a manner that is related to basic chemistry. One phase of an alloy is considered to be a homogeneous, physically and chemically separate component that is separated from the rest of the alloy by separate bonding surfaces. The alloy structure typical of nickel-based superalloys has a major phase known as γ which is the matrix of the alloy and therefore is commonly referred to as the γ matrix. The alloy structure also has a relatively large precipitate phase, known as the γ'-precipitate phase, in the γ matrix and smaller amounts of carbides, oxides and borides. It is assumed that the high temperature strength of a nickel-based superalloy, in addition to the solid solution strengthening of the γ matrix, is related to the proportion of γ 'precipitate phase present.
    The alloy elements are distributed between the phases, the distribution between the γ matrix and the γ 'precipitate being the most important. An understanding of the process of distributing elements between phases is necessary for alloy design to allow the calculation of some important alloy properties, such as the chemical composition of γ, γ ́, carbides, oxides and borides; the proportion of γ ́ that is present as γ ́ particles and as γ – γ ́ eutectic; the stability of the γ phase; and an atomic lattice mismatch between γ and γ ́.
    Analysis of a number of superalloys showed that among the alloying elements that are commonly used in the development of nickel-based superalloys, elements that disperse on the γ matrix and act as γ mixed crystal strengthening elements are chromium (Cr) , Cobalt (Co), molybdenum (Mo), tungsten (W), rhenium (Re) and iron (Fe) are. In general, refractory elements with heavy (large atoms), for example rhenium, tungsten and molybdenum, are the hardeners with the greatest efficiency at high temperatures. It is desirable to achieve solid solution strengthening without causing instability of the matrix structure. Instability, which may adversely affect alloy properties, is due to the formation of undesirable phases or precipitates at high temperatures. Therefore such phases or precipitates are avoided as much as possible.
    The second major solidification process recognized in nickel-based superalloys is precipitation hardening. The precipitate arises in the γ matrix and is known as γ ́. γ ́ is an ordered face-centered cubic compound Ni3Al, which is coherent with the nickel matrix. Elements that preferentially precipitate in the γ'-phase include aluminum (Al), titanium (Ti), tantalum (Ta), niobium (Nb) and vanadium (V).
    In some exemplary embodiments, the present nickel-based superalloys have, compared to conventional nickel-based superalloys, excellent castability, high-temperature strength and creep behavior, cyclic corrosion resistance and heat corrosion resistance. The superalloys described are also suitable for casting, directional solidification and heat treatment to produce articles, e.g. Gas turbine blades, while maintaining the basic properties of the superalloy.
    The nickel-based alloy designed accordingly and described here contains chromium, molybdenum, titanium, aluminum, cobalt, tungsten, tantalum, hafnium, niobium, boron and carbon. The nickel-based alloy is rhenium-free, which allows cost savings. In one embodiment, the nickel-base superalloy contains about 7.0 wt% (wt%) to about 12.0 wt% chromium, about 0.1 wt% to about 5 wt% molybdenum, about 0 , 2 wt% to about 4.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3 wt% to about 4.9 wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 wt% to about 0.6 wt% % Hafnium, up to about 1.0% by weight niobium, up to about 0.02% by weight boron, and up to about 0.1% by weight carbon, with nickel and incidental impurities making up the difference to 100% .
    In yet another embodiment, the nickel-based alloy contains about 8.5% by weight to about 11.0% by weight chromium, about 0.5% by weight to about 3.0% by weight molybdenum, about 0% , 5 wt% to about 3.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3.5 wt% to about 4.25 wt% cobalt , about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 wt% to about 0 , 5 wt% hafnium, up to about 1.0 wt% niobium, up to about 0.01 wt% boron, and up to about 0.07 wt% carbon, with nickel and incidental impurities making the difference 100% make up.
    In some exemplary embodiments, the chromium content of the nickel-based alloy can preferably be between about 7% by weight to about 12% by weight, or about 8.5% by weight to about 11% by weight. In some embodiments, it is desirable to maintain a balance between chromium and aluminum so that the alloy can have good resistance to both oxidation and heat corrosion. Data generated in the analysis of certain alloys described herein indicated that a limited Cr: Al ratio of from about 1.5 to about 2.5 allowed the balance of required properties. Thus, a suitable range for aluminum in certain of the alloys described can be about 4% to about 6% by weight.
    The proportion of titanium of certain of the alloys described herein can preferably be between about 0.2% by weight to about 4.5% by weight, or about 0.5% by weight to about 3.5% by weight. %. Titanium is preferably present in the proportions mentioned above, so that the Al: Ti ratio can exceed about 1, or 2, or 3, or even about 4.
    Tungsten is an alloy element suitable for high temperature strength and can be distributed either on the γ-phase or on the γ'-phase. Tungsten can be present in certain of the alloys described in proportions of from about 6.0% by weight to about 9.0% by weight.
    In some alloys according to the invention, molybdenum can take over the effect of tungsten, but has a lower density. Molybdenum can reduce the resistance to environmental influences, although this can be reduced to a minimum by balanced proportions of chromium. In some exemplary embodiments, in which chromium is present in a proportion of about 7% by weight to about 12% by weight, or about 8.5% by weight to about 11% by weight, molybdenum can preferably be present in proportions of about 0.1 wt.% to about 5 wt.%, or about 0.5 wt.% to about 3.0 wt.%, so that the added benefit of strength without significantly impairing durability against environmental influences is experienced.
    Tantalum partitions, for example titanium in nickel-based alloys, almost completely enter the γ'-phase. In some exemplary embodiments, tantalum can be preferred over titanium, since tantalum has a higher melting temperature than titanium and therefore cannot lower the melting temperature of the alloy as much as a comparable proportion of titanium. However, tantalum is a heavy element having a significantly higher density than titanium, and therefore a lighter article can be produced if a larger amount of titanium than tantalum is used. Taking these considerations into account, useful proportions of tantalum in specific exemplary embodiments of the superalloys described can be from about 4.0% by weight to about 6.5% by weight, based on the total weight of the alloy.
    Cobalt can increase the solid solubility temperature of γ ', so that the temperature-dependent properties of alloys in which it is contained are improved. Cobalt can also improve the structural stability of the alloy by preventing sigma phase precipitation. For these reasons, the alloys described herein may, in specific embodiments, include about 3.0 wt% to about 4.9 wt%, or about 3.4 wt% to about 4.25 wt% cobalt based on the total weight of the alloy.
    Hafnium can be useful as a grain boundary strengthener and can increase oxidation resistance. Therefore, in some exemplary embodiments, the alloys described herein contain hafnium in proportions of up to about 1.0% by weight, or about 0.05% by weight to about 0.5% by weight. In special exemplary embodiments, the alloys also contain niobium in proportions of up to about 1% by weight.
    The nickel-based alloy can be processed by one (or more) of any existing method to form components for a gas turbine engine, for example, but not wishing to be limited thereto, powder metallurgy methods (e.g. sintering, hot pressing, hot isostatic methods, hot vacuum bagging methods and the like ), Ingot casting, followed by directional solidification, lost wax casting, ingot casting followed by thermomechanical treatment, near-net-shape casting, chemical vapor deposition, physical vapor deposition, combinations thereof and the like.
    In a method of manufacturing a gas turbine blade using a nickel-based alloy, as described, the desired components are provided in the form of powder particles either separately or as a mixture and at a sufficient level, usually in the range of about 1350 ° C to about 1750 ° C heated lying temperature to melt the metal components. The molten metal is then poured into a mold in a casting process in order to produce the desired shape.
    As mentioned above, any casting method can be used, e.g. Block casting, lost wax casting, high gradient casting or near-net-shape casting. In the case of embodiments in which relatively complex parts are to be produced, the molten metal may preferably be cast by means of a lost wax process, which may generally be more suitable for producing parts which cannot be produced by normal production techniques, e.g. Turbine blades that have complex shapes or turbine components that have to withstand high temperatures. In another embodiment, the molten metal can be cast into turbine components using an ingot casting process. The casting process can be carried out using gravity, pressure, inert gas or vacuum conditions. In some exemplary embodiments, the casting process is carried out in a vacuum.
    After casting, the melt can advantageously be directionally solidified in the casting mold. Directional solidification generally leads to grains that are elongated in the direction of solidification and thus to a higher creep resistance for the airfoil than in the case of equiaxed casting and is suitable for use in some exemplary embodiments. Specifically, the present alloys can be formed into multi-grain directionally solidified components that are configured to accommodate a large number of grains across the cross-section of the part, the yield being significantly greater than that of conventional monocrystalline nickel-based superalloys. This means that although small components can usually be produced as a single crystal, many of the larger components of gas turbines are difficult to form as a true single crystal (SC, single crystal). Therefore, the yield of these components in SC form may not be economically viable. In contrast, the yield of a similarly sized multi-grain directionally solidified gas turbine component using the embodiments described herein can be at least about 80%, or about 80% to about 100%.
    After directional solidification, the castings, e.g. by any conventional cooling method. The cast parts that have the nickel-based alloy can then optionally be subjected to different heat treatments in order to optimize the strength and increase the creep resistance. Desirably, the heat treatment results in a casting that has a γ 'fraction of more than about 50% or even more than about 60%. The heat treatment may generally include heating the casting in vacuum to a temperature of about 1237.8 ° C (2260 ° F) to about 1315.6 ° C (2400 ° F) for 2 to 4 hours. The casting can then be furnace cooled in vacuum, argon or helium at a cooling rate of about 8.3 ° C / minute (15 ° F / minute) to about 25 ° C / minute (45 ° F / minute) to 1121.1 ° C (2050 ° F) and then blown gas cooling in vacuum, argon, or helium at about 55.6 ° C / minute (100 ° F / minute) to about 83.3 ° C / minute (150 ° F / minute) ) cooled to 648.9 ° C (1200 ° F) or below. When the temperature drops below 648.9 ° C (1200 ° F), the items can be cooled to room temperature using any cooling rate.
    In some exemplary embodiments, the castings may be subjected to an aging treatment. For example, the castings may be tempered by heating them under vacuum to 1079.4 ° C (1975 ° F) for a period of 4 hours until they are oven cooled below 648.9 ° C (1200 ° F), to about 871.1 ° C (1600 ° F) to about 898.9 ° C (1650 ° F) for 4 to 16 hours and then oven cool to room temperature.
    [0035] The nickel-based alloys described herein can thus be processed into different airfoils for large gas turbine engines. As mentioned above, the nickel base alloys described herein can provide improved casting crack resistance and a larger heat treatment window than conventional nickel base superalloys, e.g. Rene ́ N4, while this reduces manufacturing costs and increases the yield of cast elements. Articles formed from the disclosed alloys can also exhibit increased strength, ductility and creep resistance, as well as oxidation and heat corrosion resistance. As a result, such articles can be used at higher operating temperatures and / or have a longer useful life than articles which are formed using conventional nickel-based alloys.
    Examples of components or articles suitably formed using the alloys described herein include, but are not limited to, blades (or blades), non-rotating nozzles (or vanes), shrouds, combustors, and the like. Components / articles that are believed to be particularly advantageously formed from the alloys described herein include nozzles and blades. The superalloy can be used in conjunction with a variety of thermal barrier coatings.
    An exemplary method of making a cast and heat-treated industrial item, such as a large power turbine blade, using a nickel-base superalloy of the present specification can be performed generally as explained below. The desired component, e.g. a turbine blade, can be directionally cast using the superalloy. The casting may then be subjected to a heat treatment in which the blade is heated, typically in vacuum, to a temperature of about 1237.8 ° C (2260 ° F) to about 1315.6 ° C (2400 ° F) for 2 to 4 hours so that the blade has a γ'-proportion of more than about 50% or more than 60%. The blade can then be furnace cooled in vacuum, argon, or helium at a cooling rate of about 8.3 ° C / minute to 25 ° C / minute (15 ° F to about 45 ° F / minute) to about 1121.1 ° C (2050 ° F), followed by gas fan cooling in vacuum, argon, or helium at about 55.6 ° C / minute (100 ° F / minute) to about 83.3 ° C / minute (150 ° F / minute) is performed at about 648.9 ° C (1200 ° F) or below. When the temperature drops below about 648.9 ° C (1200 ° F), the one (or more) blades can be cooled to room temperature at any cooling rate. The blade (s) can then be tempered by heating it under vacuum to 1079.4 ° C (1975 ° F) to below 648.9 ° C (1200 ° F) for a period of 4 hours ) oven-cooled, heated to about 871.1 ° C (1600 ° F) to about 898.9 ° C (1650 ° F) for 4 to 16 hours, and then oven-cooled to room temperature.
    Although the superalloy of the present invention is particularly suitable for casting using directional solidification, it can be readily produced by conventional casting processes or monocrystalline casting techniques. The superalloy is ideally suited for high temperature turbine components, for example rotor blades, blades, guide vanes and the like for gas turbine engines.
    [0039] The following examples, which are intended to be exemplary and not limiting, illustrate compositions and methods of making some of the various embodiments of nickel-based alloys. In the following examples, test samples were cast in a directional solidification furnace. The mold withdrawal rate, which corresponds to the rate of solidification, was 30.48 cm (12 inches) per hour. Material properties were measured in the as-directional solidified condition with the express intention of optimizing chemistry independent of heat treatment effects.
    Example 1.
    In this example forty distinct nickel base superalloys were directionally cast and evaluated. Prior to mechanical testing, key material attributes were identified that are required for optimal performance of a gas turbine blade. A weighting factor was assigned to each attribute depending on its relative importance. The calculated and measured properties were then combined on a common, uniform scale and weighted accordingly. The sum of the weighted, non-unit attributes provided a means to rank the alloys based on their overall balance of properties. Table I gives the chemical properties of three exemplary alloys (alloy 1, alloy 2 and alloy 3) in% by weight, with nickel and impurities making up the difference to 100%. Each of these nickel-based superalloys had a pre-calculated γ'-mol fraction of over 50%. Also included is Rene ́ N4, a standard high temperature nickel base superalloy that is currently used in the manufacture of high temperature turbine components.
    Table I
    Table II presents a variety of calculated properties of the superalloy compositions. Each alloy is predicted to have a heat treatment window similar to or greater than that of the reference alloy Rene ́ N4, with improved processability and higher yield being a likely consequence. The calculated density of each alloy is compared to the reference alloy in a similar manner. A pre-calculated γ'-mole fraction is in any case higher compared to Rene'N4, which is usually desired with a view to high temperature strength.
    Table II
    Table III summarizes various material properties that were measured under the as-directionally solidified (as-DS) condition, the term “UTS, Ultimate Tensile Strength” denoting ultimate breaking strength; and the term "YS, Yield Strength" denotes the yield point.
    The castability was analyzed by means of a casting crack test according to US Pat. No. 4,169,742, the total crack length being measured at the outer diameter of a directionally solidified (about 0.1524 cm or 60 thousandths of an inch thick) thin-walled casting. Alloys which have the lowest crack value are preferred. Each of the alloys in Table III, under the limitations of this screening test, exhibit excellent resistance to cast cracking when compared to the reference alloy.
    The creep behavior of each alloy was evaluated in air at 760 ° C (1400 ° F) and 982.2 ° C (1800 ° F). A load capacity load was applied to provide 737.77 N / mm of stress at 760 ° C (1400 ° F) and 213.74 N / mm <2> (31 kiloponds per square inch) at 982.2 ° C (1800 ° F). mm <2> (107 kilopond per square inch). The plastic strain was monitored throughout the study. Table III shows improvements in times up to 2% creep which at 760 ° C (1400 ° F) are in the range 2.0-3.5 times compared to as-DS-Rene ́ N4. In addition, improvements in times of up to 2% creep at 982.2 ° C (1800 ° F) are between 2.75 times and 4.75 times compared to as-DS-Rene ́ N4. The creep strengths at every temperature are also improved by similar orders of magnitude compared to as-DS-Rene ́ N4.
    The tensile elongation behavior of each material was evaluated at 760 ° C (1400 ° F) in air. Samples were pulled to break at a fixed deformation rate of 0.508 mm / minute (0.02 in / minute). Table III gives a range of behavior compared to the reference alloy. Alloys 1 and 2 show considerable improvements in the yield point with comparable ultimate breaking strengths. With regard to the yield and tensile strengths, the results of alloy 3 are slightly worse compared to as-DS-Rene ́ N4. However, this is effectively compensated for by the excellent castability and creep behavior.
    Table III
    While only specific features of the invention have been illustrated and described herein, many modifications and changes will become apparent to those skilled in the art. It is therefore understood that the appended claims are intended to cover all modifications and changes that fall within the true scope of the invention.
    [0051] Nickel-based superalloys are created that have: about 7.0 weight percent (wt%) to about 12.0 wt% chromium, about 0.1 wt% to about 5 wt% molybdenum, for example 0.2 wt% to about 4.5 wt% titanium, about 4 wt% to about 6 wt% aluminum, about 3 wt% to about 4.9 wt% cobalt, about 6.0 wt% to about 9.0 wt% tungsten, about 4.0 wt% to about 6.5 wt% tantalum, about 0.05 wt% to about 0, 6% by weight hafnium, up to about 1.0% by weight niobium, up to about 0.02% by weight boron, and up to about 0.1% by weight carbon, with nickel and incidental impurities being the difference to 100 % form. The alloys can be cast, directionally solidified, and heat treated to produce articles with a γ 'content greater than about 50%.
    权利要求:
    Claims (8)
    [1]
    A nickel-based alloy comprising: 7.0 percent by weight,% by weight, up to 12.0 percent by weight chromium, 0.1 percent by weight to 5 percent by weight molybdenum, 0.2 percent by weight to 4.5% by weight of titanium, 4% by weight to 6% by weight of aluminum, 3% by weight to 4.9% by weight of cobalt, 6.0% by weight to 9.0% by weight. % Tungsten, 4.0 wt% to 6.5 wt% tantalum, 0.05 wt% to 0.6 wt% hafnium, to 1.0 wt% niobium, to 0 , 02 wt .-% boron, and up to 0.1 wt .-% carbon, with nickel and random impurities form the difference to 100%.
    [2]
    The nickel base alloy of claim 1, wherein the alloy has an aluminum / titanium ratio of greater than one.
    [3]
    3. cast article of an alloy according to claim 1, with a γ-content of more than 50%.
    [4]
    4. The nickel-based alloy of claim 1, comprising: 9.0 wt.% To 11.0 wt.% Chromium, 0.5 wt.% To 3.0 wt.% Molybdenum, 0.5 wt. % to 3.5 wt% titanium, 4 wt% to 6 wt% aluminum, 3.5 wt% to 4.25 wt% cobalt, 6.0 wt% to 9 , 0 wt% tungsten, 4.0 wt% to 6.5 wt% tantalum, 0.05 wt% to 0.5 wt% hafnium, to 1.0 wt% Niobium, to 0.01 wt% boron, and to 0.07 wt% carbon, with nickel and incidental impurities forming the difference to 100%.
    [5]
    The nickel base alloy of claim 4, wherein the alloy has an aluminum to titanium ratio greater than one.
    [6]
    6. cast article of an alloy according to claim 4, with a γ-content of more than 50%.
    [7]
    7. cast article according to claim 6, which is designed as a component of a gas turbine.
    [8]
    8. A method of making a cast and heat treated article comprising the steps of:Providing a nickel base alloy according to claim 1;Melting, casting and directionally solidifying the alloy to produce an article; andHeat treating the article so that the article has a γ content greater than 50%.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20120273093A1|2012-11-01|
    CN102002612A|2011-04-06|
    JP5773596B2|2015-09-02|
    CN102002612B|2016-06-29|
    US20110052443A1|2011-03-03|
    CH701641A2|2011-03-15|
    DE102010037046A1|2011-03-03|
    JP2011052323A|2011-03-17|
    US8226886B2|2012-07-24|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US12/551,294|US8226886B2|2009-08-31|2009-08-31|Nickel-based superalloys and articles|
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