• 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:
    A method for producing a workpiece, in particular a rotor, comprising: - using a base body having at least one attachment region of a first alloy, - producing a weldable fixing layer in the attachment region of the base body, and having a second alloy different from the first alloy; - providing a barrier layer between the base body and the weldable fixing layer, to avoid a reaction of the first alloy with the second alloy during a heat treatment, and heating the body of base, the barrier layer and the weldable fixing layer to connect them.
    公开号:FR3015322A1
    申请号:FR1462868
    申请日:2014-12-19
    公开日:2015-06-26
    发明作者:Andreas Burghardt；Bernd Reinsch
    申请人:Robert Bosch GmbH；
    IPC主号:
    专利说明:

    [0001] Field of the Invention The present invention relates to a method of realizing a workpiece, in particular a rotor. The invention also relates to a method for producing a composite part, in particular a rotor and the part thus obtained. STATE OF THE ART Today's internal combustion engines are increasingly using turbochargers to make diesel engines or gasoline engines much more economical and yet dynamic and comfortable. Turbine rotor materials exposed to exhaust gases are currently based on nickel (Ni) -based alloys. To improve the dynamics, titanium aluminide (TiAl) alloys are increasingly being considered which are characterized by low density (about 5g / cm3) and high specific strength. Turbine rotors based on TiAl alloy are manufactured for example by a thin casting process or a metal powder injection process also called metal injection molding process (MIM). A major challenge is to attach the TiAl alloy turbine rotor to the steel shaft connecting the turbine rotor to the air side compressor rotor. In order to assemble the Ni alloy turbine rotors with the steel shaft, the electron or laser welding processes are currently used because of the very short cycle times that these processes allow and the very high reliability the assembly of these fusion welding processes. However, the development of a brittle phase, accentuated between Ti, Fe and Al, however, prohibits the transposition of this welding process to the assembly of a turbine rotor in a TiAl-based alloy with steel. To solve this problem, the TiAl alloy turbine rotor is associated with intermediate pieces made of Ni-based alloys that can be welded to the steel. This is done for example by diffusion welding or friction welding. But these solutions are long and expensive to implement. In addition, a Ni-based alloy interlayer can be applied by a powder spraying process to allow welding on the steel. This is done for example by spraying with a cold gas or by plasma or flame at high speed. But these processes are also expensive and ultimately use only a small portion of the necessary powders and are expensive. In addition, the process does not perform metallurgical bonds between the TiAl-based alloy and the Ni-based alloy interlayer. It is not possible to attach the Ni-based alloy interlayer to the TiAl alloy turbine rotor by cofiring because of the different melting ranges of TiAl and Ni based alloys and also because of the very high reaction rate between Ni-based alloys and TiAl-based alloys. Document DE 10 2010 011 486 A1 describes an exhaust gas turbocharger rotor which, for fixing the turbine rotor to the shaft, provides an intermediate piece at least between the rotor and the shaft, this intermediate piece being a porous metal part or ceramic part which is connected to the turbine rotor and / or to the shaft by an infiltration process. SUMMARY OF THE INVENTION AND ADVANTAGES OF THE INVENTION The present invention relates to a method for making a workpiece, in particular a rotor consisting of using a base body having at least one attachment region of a first alloy, to produce a layer of weldable fastening in the attachment region of the base body, this weldable fastening layer having a second alloy different from the first alloy, providing a barrier layer between the base body and the weldable fixing layer, the barrier layer avoiding a reaction of the first alloy of the base body with the second alloy of the weldable fixing layer during a heat treatment and heating the base body, the barrier layer and the weldable fixing layer to interconnect the base body, the barrier layer and the weldable fixing layer.
    [0002] The invention also relates to a method of producing a composite part, in particular a rotor, using a part as defined above and fusion welding a shaft, in particular a piece of steel shaft in the region of the weldable fixing layer.
    [0003] Finally, the subject of the invention is the part obtained by the process defined above and in particular an exhaust gas turbocharger rotor. The method according to the invention makes it possible to produce a part, in particular a turbine rotor which is manufactured in a simple manner and securely, quickly and economically attaches to another part, in particular a steel shaft by a fusion welding process. . This is achieved by means of a barrier layer whose properties avoid any reaction of the atoms of a first alloy of a base body with the atoms of a second alloy of a weldable fixing layer in the course of time. a heat treatment. In other words, this means that the barrier layer according to the invention effectively prevents the inter-diffusion of the types of atoms of the first alloy to the second alloy. During the heat treatment, especially during the heating step, this barrier layer intervenes on both sides, that is to say on the side of the base body and the side of the weldable fixing layer to form a solid bond. There is thus a part fixing layer which is connected to the workpiece by a connection by the material without forming a brittle phase and which, on the other hand, makes it possible to connect a steel shaft by fusion welding. According to another advantageous characteristic, the first alloy is an alloy based on titanium-aluminum and the second alloy is a vanadium-based alloy (V). Since titanium aluminum alloys are characterized by low density and very high specific strength and vanadium-based alloys have the advantage of good fusion weldability, especially with a steel shaft, this makes it possible to to realize a rotor connected very simply and economically to a steel shaft by fusion welding. According to another advantageous characteristic, the barrier layer prevents the diffusion of the atoms of the first alloy of the base body towards the atoms of the second alloy of the weldable fixing layer. In other words, this means that the barrier layer has a diffusion coefficient which avoids the diffusion of the atoms of the first alloy of the base body to the atoms of the second alloy of the weldable fixing layer. This makes it possible to form the barrier layer as a diffusion barrier for the atoms of the first alloy. This means effectively avoids an intense concentration compensation of the types of atoms and, as well as an indeterminate fraction of the atoms of the first alloy, for example the titanium and aluminum components, arrive in the fusion-weldable fixing layer, which would deteriorate the characteristics of the weldability or fusion welding process or even prohibit this operation. In addition, the sintering, for example that of TiAl-based alloys is at temperatures above 1400 ° C. At such very high temperatures during the cofiring of different metal alloys, a very intense interdiffusion of balancing the concentrations of the atomic types occurs. For this reason, the metal interlayer made by co-sintering would have at the weld site, always a certain fraction of titanium and aluminum components coming from the rotor and which would not make it possible to satisfactorily apply the fusion welding process. According to another advantageous characteristic, the barrier layer prevents the diffusion of the atoms of the second alloy of the weldable fixing layer towards the atoms of the first alloy of the basic body. In other words, this means that the barrier layer has a diffusion coefficient which furthermore avoids the diffusion of the second alloy atoms of the weldable fixing layer to the atoms of the first alloy of the base body. This avoids that atoms of the fixing layer arrive uncontrollably in the bonding zone between the base body and the barrier layer, which would deteriorate the bonding by the material between the barrier layer and the base body. According to another advantageous characteristic, the barrier layer is an oxide ceramic. In particular, it is advantageous that the oxide ceramic of the barrier layer is zirconium dioxide of the general chemical formula ZrO 2 - 6, 6 being in a range greater than or equal to 0 and less than or equal to 0.5. The thickness of the ceramic barrier layer is then in a range between 0 and 2 mm. These means make it possible to form a solid bond of zirconium dioxide with the two alloys, that is to say, in particular the TiAl-based alloy and the V-based alloy. Alternatively or in addition, the ceramic The oxide may comprise yttrium oxide or magnesium oxide in an amount greater than 0% and less than or equal to 10% by weight. According to another advantageous characteristic, the weldable fixing layer also contains nickel. The addition of nickel, for example in a percentage greater than or equal to 5% and less than or equal to 30 mass%, makes it possible to adapt the fusion or sintering behavior of the second alloy, which is preferably an alloy based on vanadium V to the first alloy which is preferably a TiAl-based alloy of the rotor.
    [0004] According to another advantageous characteristic, the weldable fixing layer contains in addition to zirconium and / or titanium and / or between the barrier layer and the weldable fixing layer there is an intermediate layer containing zirconium and / or titanium and in the heating step is connected to the melt bondable fixing layer and the barrier layer. The two zirconium and titanium reactive metal elements may be added in a range greater than or equal to 0 and less than or equal to 5% by mass. The fixing layer has for example a thickness of between 0.1 and 5 mm. The intermediate layer has for example a thickness of between 0 and 0.5 mm.
    [0005] The reactive elements of zirconium and / or titanium guarantee on the one hand the development of a bond by the material with the barrier layer or diffusion barrier, in ceramic during the rise in temperature. On the other hand, the V-based alloy can be easily connected to the steel shaft by fusion welding.
    [0006] According to another advantageous characteristic, before the step of raising the temperature of the base body, this basic body is an uncured body and the weldable fixing layer, the barrier layer and, if appropriate, the intermediate layer are applied. by injection and / or spraying or spraying or printing for example by an ink, an inkjet printing or a screen printing on the base body and in the heating step of the base body is carried out the cofritting of the fusible sealable layer of the barrier layer and optionally the intermediate layer.
    [0007] Alternatively, before the step of raising the temperature of the base body, the latter is in the fried state and the barrier layer, the fusion-weldable fixing layer and, if appropriate, the intermediate layer are applied on the basic body by a thermal spraying method, eg plasma spraying, powder and flame spraying, high speed flame spraying, cold gas spraying or electric arc spraying. According to another advantageous characteristic, before the heating step, the base body and the barrier layer are in the fried state and the weldable fixing layer is in the fried state or in a state obtained by fusion metallurgy. The fried state according to the present invention means that the object is already fried before the next heating step and no longer has to undergo any further sintering operation.
    [0008] These means make it possible to produce in different ways a fusion-weldable rotor which is very economical and very effective. Drawings The present invention will be described hereinafter in more detail with the aid of a process for producing a component, in particular a rotor, and the component obtained diagrammatically shown in the accompanying drawings in which: FIG. 1 is a diagram of a rotor according to the invention obtained by the method of the invention, FIG. 2 is a schematic detail view of the fixing region of a first embodiment of the rotor. according to the invention, and - Figure 3 is a diagram of the fixing region of a second embodiment of the rotor of the invention, - Figure 4 shows a flow chart of the method of producing the component according to the invention, FIG. 5 is a simplified flow chart of a method for producing a composite part according to the invention. DESCRIPTION OF EMBODIMENTS OF THE INVENTION FIG. 1 shows a composite part according to the invention generally carrying the reference numeral 10. The com piece posite 10 is here constituted by a rotor. The rotor 10 comprises a part 12 constituting the rotor itself. The rotor 10 has a steel shaft 14. The rotor 12 has a base body 16 connected to the steel shaft 14 by an attachment region 18. The connection between the rotor 12 and the steel shaft 14 has been made by a welding process. The rotor 12 or the base body 16 has a first alloy in the attachment region 18. The base body 16 of the rotor 12 can be made completely of a first alloy. The first alloy is preferably a titanium-aluminum alloy. In order to economically and reliably secure such a rotor 16 which is characterized in particular by a low density and a high specific strength, on a steel shaft, at the attachment region 18, the rotor 10 further has, according to invention, a barrier layer 20 and a fastening layer 22 not detailed in Figure 2. According to Figure 2, the attachment region 18 of the base body 16 comprises a barrier layer 20 which is preferably directly on the base body 16. The barrier layer 20 may have a thickness of between 0 and 2 mm. On the side of the barrier layer 20 opposite the base body 16, there is the bonding layer 22 which can be welded and preferably located directly on the barrier layer 20. The solderable bonding layer 22 has a thickness between 0.1 and 5 mm. This weldable bonding layer 22 has a second alloy different from the first alloy. The second alloy is preferably a V-based alloy. According to the invention, the barrier layer 20 is located between the base body 16 and the solderable bonding layer 22; it is performed to avoid a reaction of the first alloy of the base body 16 and the second alloy of the weldable bonding layer 22 during the heat treatment, for example during the sintering operation or other step of temperature rise. The barrier layer 20 is preferably designed to prevent diffusion between the first alloy of the base body 16 to the atoms of the second alloy of the weldable bonding layer 22 during the heat treatment. The barrier layer 20 thus constitutes a diffusion barrier 20. The barrier layer 20 is further designed to prevent the diffusion of the atoms of the second alloy of the weldable bonding layer 22 into the atoms of the first alloy of the base body 16 during heat treatment, especially during sintering. Thus, the barrier layer 20 has for example a diffusion coefficient to prevent the diffusion of the atoms of the first alloy of the base body 16 towards the atoms of the second alloy of the weldable bonding layer 22 and possibly also the reverse movement during a heat treatment. In the present case, the barrier layer 20 is zirconium dioxide of the general chemical formula ZrO 2 - 6, 6 being in a range greater than or equal to 0 and less than or equal to 0.5. This in particular prevents the titanium and / or aluminum atoms from diffusing uncontrollably towards the bonding layer 22 which can lead to the formation of a brittle phase and thus deteriorate or even prevent the possibility of welding by the process of fusion welding. Figure 3 shows the attachment region 18 'of another embodiment of the component 12 or rotor 12 according to the invention. In contrast to the embodiment of FIG. 2, the rotor 12 additionally has an intermediate layer 24. The intermediate layer 24 is located between the barrier layer 20 and the fixing layer 22. The intermediate layer may have an intermediate layer 24. thickness between 0 and 0.5 mm. The intermediate layer 24 contains titanium and / or zirconium. The intermediate layer 24 guarantees, on the one hand, the development of a connection by the material with the ceramic barrier layer 20 or the diffusion barrier 20 during co-sintering. On the other hand, the vanadium alloy can be connected to the steel shaft by fusion welding. FIG. 4 shows a flow chart of the method 100 for producing a part 12 according to the invention, in particular a rotor 12.
    [0009] The method comprises the step 102 of supplying the base body 16, the step 104 of providing a weldable fixing layer 22 in the attachment region 18 of the base body 16, the step 106 of providing a layer barrier 20 between the base body 16 and the weldable fixing layer 22 and a step 108 of heating the base body 16, the weldable fixing layer 22 and the barrier layer 20. In the supply step 102, takes a base body 16 having at least one attachment region 18; 18 'of a first alloy.
    [0010] In step 104, a weldable fixing layer 22 is produced in the fastening region 18; 18 'of the base body 16 which has a second alloy, different from the first alloy. In step 106, a barrier layer is produced between the base body 16 and the weldable fixing layer 22, the barrier layer 20 avoiding a reaction of the first alloy of the base body 16 with the second alloy of the base layer 16. weldable fastener 22 during a heat treatment. In the heating step 108, the base body 16, the barrier layer 20 and the weldable fixing layer 22 are heated to bond the base body 16, the barrier layer 20 and the weldable fixing layer 22 together. to others.
    [0011] According to a process development, in step 102, a non-heat treated body 16 is used. In steps 104 and 106 it is then possible to apply the barrier layer 20, the weldable fixing layer 22 and, if appropriate, the intermediate layer 24 by injection and / or spraying, spraying or printing on the uncured body 16.
    [0012] In the heating step 108 it is then possible to co-frit the uncured body 16, the barrier layer 20, the weldable fixing layer 22 and, if appropriate, the intermediate layer 24. According to another development of the process 100, in step 102 the base body 16 is used in the finished state. In steps 104 and 106, the barrier layer 20, the weldable fixing layer 22 and, if appropriate, the intermediate layer 24 are then applied by a thermal spraying method on the base body 16, fried. Then, in the heating step 108, the heat-treated base body 16, the barrier layer 20, the weldable fixing layer 22 and, if appropriate, the intermediate layer 24 are connected to each other by heat treatment. According to another development of the method 100 of the invention, in the steps 102 and 106 is used the base body 16 and the barrier layer 20 in the finished state. In step 104, the solderable fixing layer 22 is in a fried state or obtained by melting metallurgy. In the heating step 108, the fritted base body 16, the fritted barrier layer 20, the fried or melted metallurgy fixing layer 22 and, if appropriate, the intermediate layer 24 are connected together by a subsequent heat treatment.
    [0013] FIG. 5 shows a flowchart of a method 200 for producing a composite part 10, in particular a rotor 10 according to an exemplary embodiment of the invention. The method 200 comprises the step 202 of providing the part 12 or the rotor 12 and a step 204 consisting of fusion welding, the shaft 14, in particular the steel shaft 14 on the part 12 or on the fixing layer Weldable 22 of part 12.15 NOMENCLATURE OF MAIN ELEMENTS 10 Composite part / rotor 12 Part 14 Steel shaft 16 Base body 18 Fixing region 20 Barrier layer 22 Fixing layer 24 Intermediate layer 102-108 Process step 100 202-204 Step of the 20015 process
    权利要求:
    Claims (15)
    [0001]
    CLAIMS1 °) A method (100) for producing a workpiece (12), in particular a rotor (12) comprising the following steps: - using (102) a base body (16) having at least one attachment region (18, 18 ') of a first alloy, - producing (104) a weldable fixing layer (22) in the fixing region (18, 18') of the base body (16), this weldable fixing layer (22) having a second alloy different from the first alloy; - providing (106) a barrier layer (20) between the base body (16) and the weldable fixing layer (22), the barrier layer (20) evoking a reaction of the first alloy of the base body (16) with the second alloy of the weldable fixing layer (22) during a heat treatment, and - heating (108) the base body (16), the barrier layer (20) and the weldable fixing layer (22) for interconnecting the base body (16), the barrier layer (20) and the weldable fixing layer (22).
    [0002]
    2) Method (100) according to claim 1, characterized in that the first alloy is a titanium-aluminum alloy.
    [0003]
    3) Method (100) according to claim 1, characterized in that the second alloy is a vanadium-based alloy.
    [0004]
    4) Method (100) according to claim 1, characterized in that the barrier layer (20) blocks the diffusion of the atoms of the first alloy of the base body (16) to the atoms of the second alloy of the weldable fixing layer (22) during heating (108).
    [0005]
    Method (100) according to Claim 4, characterized in thatthe barrier layer (20) blocks the diffusion of the atoms of the second alloy of the weldable fixing layer (22) towards the atoms of the first alloy of the basic body ( 16) during heating (108).
    [0006]
    6. Process (100) according to claim 1, characterized in that the barrier layer (20) is an oxide ceramic.
    [0007]
    Process (100) according to claim 6, characterized in that the oxide ceramic of the barrier layer (20) is zirconium dioxide of the general formula ZrO 2 - 6, 8 being in a range greater than or equal to 0 and lower or equal to 0.5 and / or yttrium oxide or magnesium oxide in a range greater than or equal to 0 and less than or equal to 10% by mass.
    [0008]
    8 °) Method (100) according to claim 1, characterized in that the weldable fixing layer (22) contains nickel.
    [0009]
    Process (100) according to claim 1, characterized in that the weldable fixing layer (22) contains at least zirconium and / or titanium and / or an intermediate layer (24) between the barrier layer (20). ) and the weldable fixing layer (22), this intermediate layer comprising zirconium and / or titanium, and in the heating step (108) this layer is connected to the weldable fixing layer (22) and to the the barrier layer (20).
    [0010]
    Process according to Claim 1 or Claim 9, characterized in that before the heating step (108) the base body (16) is an uncured body (16) and the barrier (20), the weldable fixing layer (22) and optionally the intermediate layer (24) are applied by injection and / or printing on the base body (16), and - in the heating step (108). ) the uncured body (16), the barrier layer (20), the weldable fixing layer (22) and optionally the intermediate layer (24) are co-sintered.
    [0011]
    Method according to Claim 1 or Claim 9, characterized in that before the heating step (108) the base body (16) is in the fried state and the barrier layer ( 20), the weldable fixing layer (22) and, if appropriate, the barrier layer (24) are applied to the base body (16) by a thermal spraying method.
    [0012]
    Process according to Claim 1, characterized in that, before the heating step, the base body (16) and the barrier layer (20) are in the fried state and the weldable fixing layer (22) is in the fried state or in a state made in melt metallurgy.
    [0013]
    13 °) Part (12), in particular rotor (12) made with the method of any one of claims 1 to 12.
    [0014]
    14 °) Method (100) for producing a composite part (10), in particular a rotor (10) comprising the following steps: - using (202) a part (12) according to claim 13, and - fusion welding (204) a shaft (14), in particular a steel shaft (14) to the workpiece (12) in the region of the weldable fixing layer (22).
    [0015]
    15 °) composite part (12), in particular rotor (10) produced according to claim 14.35
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JPH049753B2|1984-04-20|1992-02-21|
    JPH0829990B2|1988-09-21|1996-03-27|日本特殊陶業株式会社|Bonded body of ceramics and metal|
    DE4116088A1|1991-05-16|1992-11-19|Forschungszentrum Juelich Gmbh|METHOD FOR JOINING STEEL WITH ALUMINUM OR TITANIUM ALLOY PARTS AND TURBOCHARGERS RECEIVED AFTER|
    US5630314A|1992-09-10|1997-05-20|Hitachi, Ltd.|Thermal stress relaxation type ceramic coated heat-resistant element|
    US5558922A|1994-12-28|1996-09-24|General Electric Company|Thick thermal barrier coating having grooves for enhanced strain tolerance|
    US6924040B2|1996-12-12|2005-08-02|United Technologies Corporation|Thermal barrier coating systems and materials|
    US6117560A|1996-12-12|2000-09-12|United Technologies Corporation|Thermal barrier coating systems and materials|
    FR2776215B1|1998-03-20|2000-06-16|Snecma|PROCESS FOR MANUFACTURING A HIGH-THERMAL FLOW REGENERATIVE CIRCUIT, IN PARTICULAR FOR A FIREPLACE COMBUSTION CHAMBER|
    EP1002935A1|1998-11-20|2000-05-24|Asea Brown Boveri AG|TiAl-rotor of a turbomachine and method of manufacturing|
    US7198832B2|1999-10-25|2007-04-03|Vitex Systems, Inc.|Method for edge sealing barrier films|
    US6866901B2|1999-10-25|2005-03-15|Vitex Systems, Inc.|Method for edge sealing barrier films|
    US6455167B1|1999-07-02|2002-09-24|General Electric Company|Coating system utilizing an oxide diffusion barrier for improved performance and repair capability|
    CN1277650C|2001-09-28|2006-10-04|古河Sky株式会社|Method of brazing aluminum or aluminum alloy materials and aluminum alloy brazing sheet|
    DE10209347B4|2002-03-02|2005-12-08|Daimlerchrysler Ag|Manufacturing method for a turbine rotor|
    US6921014B2|2002-05-07|2005-07-26|General Electric Company|Method for forming a channel on the surface of a metal substrate|
    CN1238150C|2002-10-21|2006-01-25|哈尔滨工业大学|Active compound gradient separation diffusion welding method for titanium aluminium base alloy and steel|
    JP3865705B2|2003-03-24|2007-01-10|トーカロ株式会社|Heat shielding coating material excellent in corrosion resistance and heat resistance, and method for producing the same|
    US7094450B2|2003-04-30|2006-08-22|General Electric Company|Method for applying or repairing thermal barrier coatings|
    US7078073B2|2003-11-13|2006-07-18|General Electric Company|Method for repairing coated components|
    US20050142393A1|2003-12-30|2005-06-30|Boutwell Brett A.|Ceramic compositions for thermal barrier coatings stabilized in the cubic crystalline phase|
    US6858334B1|2003-12-30|2005-02-22|General Electric Company|Ceramic compositions for low conductivity thermal barrier coatings|
    US6887595B1|2003-12-30|2005-05-03|General Electric Company|Thermal barrier coatings having lower layer for improved adherence to bond coat|
    US20070160859A1|2006-01-06|2007-07-12|General Electric Company|Layered thermal barrier coatings containing lanthanide series oxides for improved resistance to CMAS degradation|
    JP2008202544A|2007-02-21|2008-09-04|Mitsubishi Heavy Ind Ltd|Manufacturing method of rotor, and exhaust turbocharger having the rotor|
    JP5062832B2|2007-12-28|2012-10-31|富士通株式会社|Method for manufacturing magnetoresistive element|
    DE102008059617A1|2008-11-28|2010-06-02|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Rotor for exhaust-gas turbocharger of internal-combustion engine of motor vehicle, has bush radially connected inside shaft and outside turbine wheel, where bush is soldered or welded with shaft|
    US8184411B2|2009-10-26|2012-05-22|Headway Technologies, Inc.|MTJ incorporating CoFe/Ni multilayer film with perpendicular magnetic anisotropy for MRAM application|
    DE102010011486A1|2010-03-16|2011-09-22|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Rotor for a charging device|
    FR2957545B1|2010-03-19|2012-07-27|Snecma|METHOD FOR MAKING A METALLIC INSERT FOR PROTECTING AN ATTACK EDGE IN COMPOSITE MATERIAL|
    JP5908492B2|2010-12-02|2016-04-26|テトラ・ラヴァル・ホールディングス・アンド・ファイナンス・ソシエテ・アノニムＴｅｔｒａ Ｌａｖａｌ Ｈｏｌｄｉｎｇｓ ＆ Ｆｉｎａｎｃｅ Ｓ．Ａ．|Electron exit window foil, electron beam generator, method for providing electron exit window foil, and method for providing high performance electron beam device|
    US8876481B2|2011-01-05|2014-11-04|General Electric Company|Turbine airfoil component assembly for use in a gas turbine engine and methods for fabricating same|
    CN102259217A|2011-02-15|2011-11-30|洛阳双瑞精铸钛业有限公司|Method for welding rotor and steel shaft of high-niobium titanium aluminum turbocharger|
    US9945036B2|2011-03-22|2018-04-17|General Electric Company|Hot corrosion-resistant coatings and components protected therewith|
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    EP2644824A1|2012-03-28|2013-10-02|Siemens Aktiengesellschaft|Method for producing and restoring of ceramic thermal barrier coatings in gas turbines and related gas turbine|
    CN104704200B|2012-10-05|2016-12-14|西门子公司|For manufacturing the method for the second gas turbine and for the method running gas turbine facility|
    US20150233256A1|2013-01-15|2015-08-20|General Electric Company|Novel architectures for ultra low thermal conductivity thermal barrier coatings with improved erosion and impact properties|DE102012207271A1|2012-05-02|2013-11-07|Robert Bosch Gmbh|A method of connecting a shaft to a rotating member and a turbocharger shaft made by this method|
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    US10702939B2|2018-04-05|2020-07-07|Hamilton Sundstrand Corporation|Cold-spray braze material deposition|
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    优先权:
    申请号 | 申请日 | 专利标题
    DE102013226594.8A|DE102013226594A1|2013-12-19|2013-12-19|Method for producing an impeller and a rotor|
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