EP0574727B1 - Méthode de production d'un élément réfractaire à partir de deux matériaux différents - Google Patents

Méthode de production d'un élément réfractaire à partir de deux matériaux différents Download PDF

Info

Publication number
EP0574727B1
EP0574727B1 EP93108243A EP93108243A EP0574727B1 EP 0574727 B1 EP0574727 B1 EP 0574727B1 EP 93108243 A EP93108243 A EP 93108243A EP 93108243 A EP93108243 A EP 93108243A EP 0574727 B1 EP0574727 B1 EP 0574727B1
Authority
EP
European Patent Office
Prior art keywords
alloy
section
component
pressing
alloys
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP93108243A
Other languages
German (de)
English (en)
Other versions
EP0574727A1 (fr
Inventor
Peter Dr. Ernst
Manfred Dr. Thumann
Christoph Tönnes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Alstom SA
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0574727A1 publication Critical patent/EP0574727A1/fr
Application granted granted Critical
Publication of EP0574727B1 publication Critical patent/EP0574727B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12021—All metal or with adjacent metals having metal particles having composition or density gradient or differential porosity
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/1216—Continuous interengaged phases of plural metals, or oriented fiber containing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/1216—Continuous interengaged phases of plural metals, or oriented fiber containing
    • Y10T428/12174—Mo or W containing

Definitions

  • the invention is based on a component for high Temperatures, in particular from a turbine blade, according to the introductory part of claim 1.
  • Such a component and a method for producing a such a component are described in DE 28 13 892 A1.
  • the Component described is designed as a turbine impeller, which is achieved by hot pressing metal powders with different Particle structures and different chemical Compositions has been made.
  • this turbine impeller was mechanical as a starting material for the blades pretreated powder of a nickel base superalloy, such as for example the alloy IN 792, with particles in the form flattened beads used.
  • As starting material for the Impeller was a mechanically not pretreated powder another nickel-based superalloy, such as of alloy IN 100, used with spherical particles.
  • the powder Due to the structure and chemical composition of the The powder is characterized by a good starting powder Corrosion resistance at high temperatures the impeller disc has high tensile strength and good Fatigue resistance.
  • starting materials for the Turbine impellers are, however, only suitable alloys that like the very related nickel-based superalloys without Changing their structure and thus their properties exposed to high temperatures during hot isostatic pressing can be. Therefore, when making this Alloys are not used for the turbine impeller excellent properties for different ones Have tasks, but only if they differ considerably deviating temperatures can be hot compressed.
  • the invention as specified in claims 1 and 5 is based on the task of a component, in particular to specify a turbine blade of the type mentioned at the outset, which operate when used in a high temperature Device, such as in particular a gas turbine is characterized by a long service life and at the same time a way to point, which makes it possible to simplify such a component and to be suitable for mass production.
  • the component according to the invention is distinguished from comparable Components according to the state of the art by long service life. On the one hand, this is due to the fact that differently stressed parts of the component from different specified alloys exist, which correspond to the different stresses on the parts of the component are adjusted. Secondly, these alloys are selected that when hot compacting it becomes a bimetallic Composite material form a boundary layer of high strength.
  • the Component according to the invention can therefore with great certainty absorb high thermal and mechanical loads, as they do for example when operating a gas turbine or a compressor Turbocharger occur.
  • the one used to manufacture the components according to the invention is characterized in that the hot compression is carried out at temperatures at which the for desired physical or chemical properties desired structure of the alloys even with a large one Certainty is present if the ones that form the starting powder Alloys are very different chemical Have compositions.
  • FIG. 1 and 2 and each as Turbine blade 1 designed components each contain one elongated airfoil 2 and one at one end of the Blade 2 molded blade root 3.
  • Reference numeral 4 denotes a press can.
  • This Press can encloses the in the embodiment according to Fig.1 Blade root 3 and has one filled by the blade 2 Opening 5, which is preferably by welding or Soldering the press can 4 to the airfoil 2 gas-tight is completed.
  • the press can 4 encloses the entire turbine blade 1.
  • the turbine blade 1 shown in FIG. 1 is produced as follows: A cast body designed as an airfoil 2 is guided with its one end through the opening 5 into the press can 4.
  • the press can 4 which is preferably made of steel, is soldered or welded to the cast body in a gas-tight manner in the region of the opening 5.
  • a cavity of the press can which accommodates the blade root of the turbine blade 1, is filled with alloy powder.
  • the press can 4 is then evacuated and sealed gas-tight.
  • Doped gamma titanium aluminides are used as the material for the cast body and for the powder alloys based on Titanium or nickel used.
  • the one that forms the cast body Alloy is advantageously a gamma titanium aluminide with one Proportion of at least 0.5 and at most 8 atomic percent Dopant, such as one or more of the elements B, C, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr.
  • a typical alloy is 48 Atomic percent Al, 2 to 4 atomic percent chromium and the rest besides has unavoidable impurities Ti.
  • Typical alloys included in addition to unavoidable impurities and Ti either 6 Atomic percent Al and 4 atomic percent V or 24 atomic percent Al and 11 atomic percent Nb.
  • the nickel-based alloy used in the form of powder can for example the alloy IN 792 (composition in Weight percent Ni -0.12 C - 12.4 Cr - 9.0 Co - 1.9 Mo - 3.8 W - 3.9 Ta - 3.1 Al - 4.5 Ti - 0.2 B - 0.1 Zr).
  • the size of the powder particles is for all powders used less than 500 ⁇ m.
  • Such titanium and nickel-based alloys are characterized by good ductility (> 10%) Room temperature.
  • the mechanical resistance of the titanium base alloys however, this is not the case at high temperatures as high as that of gamma titanium aluminides.
  • Nickel based alloys however, have a much higher density than gamma titanium aluminides.
  • the finished by gas-tight closing of the press jug 4 Sample was placed in a press and at Use of a titanium base alloy at temperatures between 900 and 980 ° C hot isostatically compressed.
  • a typical one Pressing process at approx. 950 ° C lasted at a pressure of approx. 200 MPa about 3 hours.
  • the two alloys were under Formation of a boundary layer 6 pore-free to a bimetallic Composite material compressed.
  • the structure and the are from the micrograph according to FIG Microstructure of a part of the frame indicated in Fig. 2 To remove turbine blade according to the invention. From this is it can be seen that the alloy forming the airfoil 2 a coarse-grained alloy that forms the blade root 3 has a fine-grained microstructure and that the boundary layer 6 connecting both alloys is almost unstructured and according to chemical analysis in the essentially of a binary TiAl alloy with a proportion of approximately 25 atomic percent Al is formed.
  • the alloy forming the airfoil 2 has a ductility of approximately 0.5 to 1% at room temperature, while the alloy forming the airfoil 3 has a ductility of 18 to 20%. At a temperature of approximately 700 ° C., the airfoil 2 has a creep resistance which is considerably higher than the creep resistance of the nickel-base superalloys usually used in this temperature range.
  • the turbine blade 1 shows a ductility of 0.5 to 1% corresponding to the material of the blade leaf 2, which means that the ductility of the blade is not negatively influenced by the boundary layer 6.
  • the turbine blade 1 according to the invention is therefore characterized by a blade root 3 with high ductility and an airfoil 2 which is brittle at room temperature but has a high creep resistance at high temperatures.
  • the strength of the boundary layer 6 is sufficient to ensure safe operation of the turbine blade 1 at high temperatures.
  • a body made of a hot isostatic compacted powder are introduced.
  • a body made of a hot isostatic compacted powder were approximately 100 g an alloy powder with 48 atom percent Al, 3 atom percent Cr, balance Ti and small amounts of impurities Temperatures between 1050 and 1300 ° C and a pressure of approx. 250 MPa hot isostatically compressed for approx. 3 hours. The compacted powder was then at temperatures heat treated between 1300 and 1400 ° C for a few hours. Of the resulting body was then shown in Figure 2 Press can 4 brought and at those described there Conditions together with that forming the blade root 3 Powder is hot isostatically compressed. The according to that Heat treatment and corresponding post-processing resulting turbine blade pointed towards the Turbine blade according to Figure 2 with consistently good Creep resistance increased ductility by approx. 50% Blade 2 at room temperature.
  • the Gamma titanium aluminide existing blade one blade root 3 molded from a nickel-based alloy.
  • the Press can 4 was evacuated and sealed gas-tight.
  • hot isostatic pressing for approx. 3 hours at approx. 1000 up to 1250 ° C and a pressure of approx. 250 MPa pore-free bimetallic composite material made from after removing the press can 4, after heat treatment approx. 700 ° to 800 ° C and post-processing to remove material a turbine blade was manufactured according to the invention. At this turbine blade showed the boundary layer 6 in particular good strength.
  • a press can 4 as a form for receiving the alloys to use a sintered mold, and compacting to Achieve turbine blade in a sintering process.
  • the invention is not limited to turbine blades. she also refers to others mechanically at high temperatures heavily loaded components, such as integrally formed Turbocharger turbine wheels.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Elément pouvant être exposé à des températures élevées, en particulier aube (1) de turbine, comportant un corps d'élément comprenant au moins une première partie (emplanture d'aube 3) et au moins une deuxième partie (pale 2), dans lequel la première partie (3) est formée d'un matériau ductile et la deuxième partie (2) présente un matériau cassant par rapport au matériau ductile et chacun de ces deux matériaux contient l'un de deux alliages de compositions chimiques différentes, qui sont comprimés à température élevée en un matériau composite bimétallique avec formation d'une interface (6) reliant la première (3) et la deuxième (2) parties, le premier des deux alliages, qui forme la première partie, contenant principalement du titane et/ou du nickel, et le deuxième des deux alliages, qui forme la deuxième partie, étant une aluminite de titane gamma et présentant une proportion d'agent de dopage d'au moins 0,5 et au plus 8 pour cent en atomes.
  2. Elément suivant la revendication 1, caractérisé en ce que le deuxième alliage contient, comme agent de dopage, au moins un ou plusieurs des éléments B, C, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W et Zr.
  3. Elément suivant l'une quelconque des revendications 1 et 2, caractérisé en ce que le premier alliage, outre le titane, contient également de l'aluminium et du vanadium ou de l'aluminium et du niobium.
  4. Elément suivant l'une quelconque des revendications 1 à 3, caractérisé en ce que les première et deuxième parties sont imbriquées l'une dans l'autre au niveau de l'interface (6).
  5. Méthode de production de l'élément suivant la revendication 1, caractérisée en ce que, avant la compression à température élevée, un corps coulé à partir du deuxième alliage ou produit par la compression à température élevée de poudre du deuxième alliage est engagé par au moins une extrémité dans un moule réalisé sous la forme d'un cylindre de compression (4), et en ce que le premier alliage est versé dans le cylindre de compression sous la forme de poudre et mis en contact avec l'extrémité du corps située à l'intérieur du cylindre de compression (4).
  6. Méthode suivant la revendication 5, caractérisée en ce que le cylindre de compression (4) présente une ouverture (5) remplie par le corps engagé, qui est de préférence fermée par soudage ou brasage du cylindre de compression (4) au corps.
  7. Méthode suivant l'une quelconque des revendications 5 et 6, caractérisée en ce que la compression à température élevée est réalisée en utilisant un premier alliage à base de titane à des températures comprises entre 900 et 980°C.
  8. Méthode suivant l'une quelconque des revendications 5 et 6, caractérisée en ce que la compression à température élevée est réalisée en utilisant un premier alliage à base de nickel à des températures comprises entre 1100 et 1250°C.
  9. Méthode suivant l'une quelconque des revendications 7 et 8, caractérisée en ce que le matériau composite produit par la compression à température élevée est traité à chaud à des températures comprises entre 700 et 800°C.
EP93108243A 1992-06-13 1993-05-21 Méthode de production d'un élément réfractaire à partir de deux matériaux différents Expired - Lifetime EP0574727B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4219469A DE4219469A1 (de) 1992-06-13 1992-06-13 Hohen Temperaturen aussetzbares Bauteil, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils
DE4219469 1992-06-13

Publications (2)

Publication Number Publication Date
EP0574727A1 EP0574727A1 (fr) 1993-12-22
EP0574727B1 true EP0574727B1 (fr) 1998-08-26

Family

ID=6461000

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93108243A Expired - Lifetime EP0574727B1 (fr) 1992-06-13 1993-05-21 Méthode de production d'un élément réfractaire à partir de deux matériaux différents

Country Status (4)

Country Link
US (1) US5395699A (fr)
EP (1) EP0574727B1 (fr)
JP (1) JPH06172816A (fr)
DE (2) DE4219469A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105014068A (zh) * 2015-08-06 2015-11-04 潘桂枝 一种双金属复合材料的制备方法

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6551064B1 (en) 1996-07-24 2003-04-22 General Electric Company Laser shock peened gas turbine engine intermetallic parts
DE19710592A1 (de) * 1997-03-14 1998-09-17 Forschungszentrum Juelich Gmbh Oxidationsbeständige, TiAl-haltige Legierungen
DE19756354B4 (de) * 1997-12-18 2007-03-01 Alstom Schaufel und Verfahren zur Herstellung der Schaufel
DE19933633A1 (de) * 1999-07-17 2001-01-18 Abb Alstom Power Ch Ag Hochtemperaturlegierung
DE10054229B4 (de) * 2000-11-02 2018-06-28 Ansaldo Energia Ip Uk Limited Hochtemperaturlegierung
US7566415B2 (en) * 2002-11-18 2009-07-28 Adma Products, Inc. Method for manufacturing fully dense metal sheets and layered composites from reactive alloy powders
US6852273B2 (en) * 2003-01-29 2005-02-08 Adma Products, Inc. High-strength metal aluminide-containing matrix composites and methods of manufacture the same
US7241416B2 (en) * 2003-08-12 2007-07-10 Borg Warner Inc. Metal injection molded turbine rotor and metal injection molded shaft connection attachment thereto
RU2272912C2 (ru) * 2004-03-09 2006-03-27 Федеральное государственное унитарное предприятие "Турбонасос" Рабочее колесо осевой газовой турбины для кислородно-керосинового жидкостного ракетного двигателя
US20060083653A1 (en) * 2004-10-20 2006-04-20 Gopal Das Low porosity powder metallurgy produced components
US20070003416A1 (en) * 2005-06-30 2007-01-04 General Electric Company Niobium silicide-based turbine components, and related methods for laser deposition
JP2008202544A (ja) * 2007-02-21 2008-09-04 Mitsubishi Heavy Ind Ltd ロータの製造方法及びこのロータをそなえた排気ターボ過給機
EE05653B1 (et) 2010-04-29 2013-04-15 O� Skeleton Technologies Ssinikkomposiitelektrood elektrilise kaksikkihi kondensaatorile
DE102010042889A1 (de) * 2010-10-25 2012-04-26 Manfred Renkel Turboladerbauteil
US8944762B2 (en) 2011-10-28 2015-02-03 United Technologies Corporation Spoked spacer for a gas turbine engine
US9938831B2 (en) 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine
WO2016022139A1 (fr) 2014-08-08 2016-02-11 Siemens Aktiengesellschaft Système de pressage isostatique à chaud pour l'assemblage d'éléments modulaires utilisables dans un moteur à turbine
US10422228B2 (en) 2016-04-12 2019-09-24 United Technologies Corporation Manufacturing a monolithic component with discrete portions formed of different metals
US20190040749A1 (en) * 2017-08-01 2019-02-07 United Technologies Corporation Method of fabricating a turbine blade
RU178967U1 (ru) * 2017-10-31 2018-04-24 федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" Лопатка турбомашины из алюминиевого сплава с упрочняющим слоем, содержащим углерод
US12173615B2 (en) 2020-02-14 2024-12-24 Rtx Corporation Multi-zone blade fabrication
EP4105438B1 (fr) 2021-06-18 2026-04-08 RTX Corporation Méthode de collage pour la réparation d'une pièce d'un moteur à turbine à gaz
EP4105450A1 (fr) 2021-06-18 2022-12-21 Raytheon Technologies Corporation Système de contrôle de jeu passif produite par une technologie par frittage assisté par champ électrique (fast)
EP4105449A1 (fr) 2021-06-18 2022-12-21 Raytheon Technologies Corporation Configuration hybride collée pour le joint d'air extérieur d'une aube (boas)
US12055056B2 (en) 2021-06-18 2024-08-06 Rtx Corporation Hybrid superalloy article and method of manufacture thereof

Family Cites Families (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB608766A (en) * 1944-12-01 1948-09-21 Bbc Brown Boveri & Cie Improvements in turbine blades
US2431660A (en) * 1944-12-01 1947-11-25 Bbc Brown Boveri & Cie Turbine blade
FR1052893A (fr) * 1951-02-07 1954-01-28 Plansee Metallwerk Aube de turbine à grande résistance à la chaleur et à l'inflammation utilisable en particulier dans les turbines à gaz, et son procédé de fabrication
US2946680A (en) * 1955-08-10 1960-07-26 Thompson Ramo Wooldridge Inc Powder metallurgy
AT309154B (de) * 1970-11-24 1973-08-10 Plansee Metallwerk Werkstoff für Turbinenschaufeln
CH544217A (de) * 1971-04-08 1973-11-15 Bbc Sulzer Turbomaschinen Gasturbinenschaufel
FR2149990A5 (en) * 1971-08-09 1973-03-30 Imp Metal Ind Kynoch Ltd Metal parts prodn from several elements - eg for aircraft using process which reduces fatigue
US3940268A (en) * 1973-04-12 1976-02-24 Crucible Inc. Method for producing rotor discs
US3992200A (en) * 1975-04-07 1976-11-16 Crucible Inc. Method of hot pressing using a getter
US4063939A (en) * 1975-06-27 1977-12-20 Special Metals Corporation Composite turbine wheel and process for making same
US4097276A (en) * 1975-07-17 1978-06-27 The Garrett Corporation Low cost, high temperature turbine wheel and method of making the same
GB1582651A (en) * 1977-04-01 1981-01-14 Rolls Royce Products formed by powder metallurgy and a method therefore
DE2737248C2 (de) * 1977-08-18 1985-09-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Bauteil hoher Festigkeit mit komplizierter geometrischer Form und Verfahren zu dessen Herstellung
US4294615A (en) * 1979-07-25 1981-10-13 United Technologies Corporation Titanium alloys of the TiAl type
US4323394A (en) * 1979-08-06 1982-04-06 Motoren-Und Turbinen-Union Munchen Gmbh Method for manufacturing turborotors such as gas turbine rotor wheels, and wheel produced thereby
SE8000750L (sv) * 1980-01-30 1981-07-31 Bulten Kanthal Ab Varmhallfast maskinkomponent och sett att framstella densamma
DE3010299C2 (de) * 1980-03-18 1981-07-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Kapsel für das heißisostatische Pressen und Verfahren zum heißisostatischen Pressen unter Verwendung der Kapsel
US4663241A (en) * 1980-09-08 1987-05-05 United Technologies Corporation Powder metal disk with selective fatigue strengthening
JPS57155338A (en) * 1981-03-23 1982-09-25 Hitachi Ltd Metallic body with alloy coating resistant to corrosion and thermal shock
SE446606B (sv) * 1981-08-27 1986-09-29 Stal Laval Turbin Ab Sett att framstella skovelringar och skivor med skovlar for roterande maskiner sasom kompressorer eller turbiner
US4492737A (en) * 1982-03-05 1985-01-08 Rolls-Royce Limited Composite metallic and non-metallic articles
US4526747A (en) * 1982-03-18 1985-07-02 Williams International Corporation Process for fabricating parts such as gas turbine compressors
US4529452A (en) * 1984-07-30 1985-07-16 United Technologies Corporation Process for fabricating multi-alloy components
DE3511673A1 (de) * 1985-03-18 1986-09-18 Josef Gartner & Co, 8883 Gundelfingen Verbundprofil
US4680160A (en) * 1985-12-11 1987-07-14 Trw Inc. Method of forming a rotor
DE3543831A1 (de) * 1985-12-12 1987-07-02 Aluminium Walzwerke Singen Verbundprofil, insbesondere verbundstromschiene
US4787821A (en) * 1987-04-10 1988-11-29 Allied Signal Inc. Dual alloy rotor
US4900635A (en) * 1987-07-27 1990-02-13 Williams International Corporation Multi-alloy turbine rotor disk
JPS6447828A (en) * 1987-08-12 1989-02-22 Agency Ind Science Techn Turbin disk by super plastic forging of different alloys
US4851053A (en) * 1988-05-06 1989-07-25 The United States Of America As Represented By The Secretary Of The Air Force Method to produce dispersion strengthened titanium alloy articles with high creep resistance
US4828793A (en) * 1988-05-06 1989-05-09 United States Of America As Represented By The Secretary Of The Air Force Method to produce titanium alloy articles with high fatigue and fracture resistance
US4897127A (en) * 1988-10-03 1990-01-30 General Electric Company Rapidly solidified and heat-treated manganese and niobium-modified titanium aluminum alloys
US4904546A (en) * 1989-04-03 1990-02-27 General Electric Company Material system for high temperature jet engine operation
US4916028A (en) * 1989-07-28 1990-04-10 General Electric Company Gamma titanium aluminum alloys modified by carbon, chromium and niobium
CA2025272A1 (fr) * 1989-12-04 1991-06-05 Shyh-Chin Huang Alliages d'aluminure de titane a haute teneur en niobium
US5080860A (en) * 1990-07-02 1992-01-14 General Electric Company Niobium and chromium containing titanium aluminide rendered castable by boron inoculations
US5098653A (en) * 1990-07-02 1992-03-24 General Electric Company Tantalum and chromium containing titanium aluminide rendered castable by boron inoculation
DE59103639D1 (de) * 1990-07-04 1995-01-12 Asea Brown Boveri Verfahren zur Herstellung eines Werkstücks aus einer dotierstoffhaltigen Legierung auf der Basis Titanaluminid.
US5113583A (en) * 1990-09-14 1992-05-19 United Technologies Corporation Integrally bladed rotor fabrication
US5098484A (en) * 1991-01-30 1992-03-24 The United States Of America As Represented By The Secretary Of The Air Force Method for producing very fine microstructures in titanium aluminide alloy powder compacts
EP0513407B1 (fr) * 1991-05-13 1995-07-19 Asea Brown Boveri Ag Procédé de fabrication d' une aube de turbine
US5226985A (en) * 1992-01-22 1993-07-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105014068A (zh) * 2015-08-06 2015-11-04 潘桂枝 一种双金属复合材料的制备方法

Also Published As

Publication number Publication date
US5395699A (en) 1995-03-07
EP0574727A1 (fr) 1993-12-22
JPH06172816A (ja) 1994-06-21
DE59308916D1 (de) 1998-10-01
DE4219469A1 (de) 1993-12-16

Similar Documents

Publication Publication Date Title
EP0574727B1 (fr) Méthode de production d'un élément réfractaire à partir de deux matériaux différents
EP0513407B1 (fr) Procédé de fabrication d' une aube de turbine
DE69935891T2 (de) Verfahren zur Herstellung eines Motorhubventils
DE19681358B4 (de) Pulvergemisch aus Aluminiumlegierung sowie gesinterte Aluminiumlegierungen
DE3445767C2 (fr)
DE69628786T2 (de) Eisenaluminid für elektrische Widerstandsheizelemente
DE2503165C2 (de) Verfahren zur Herstellung eines Sinterkörpers mit örtlich unterschiedlichen Materialeigenschaften und Anwendung des Verfahrens
EP3069802B1 (fr) Procédé de production d'un composant en matériau composite doté d'une matrice en métal et de phases intercalaires inter-métalliques
DE3780136T2 (de) Gesinterter verbundpresskoerper mit grosser haerte.
DE69915797T2 (de) Verfahren zur herstellung dichter teile durch uniaxiales pressen agglomerierter kugelförmiger metallpulver.
EP0574708B1 (fr) Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément
DE602004005976T2 (de) Herstellungsverfahren für nieten aus kryogen zerkleinerten aluminiumlegierungen und auf diese weise hergestellte nieten
DE19756354B4 (de) Schaufel und Verfahren zur Herstellung der Schaufel
DE2542094A1 (de) Metallpulver, verfahren zur behandlung losen metallpulvers und verfahren zur herstellung eines verdichteten presslings
DE2813892B2 (de) Verfahren zur pulvermetallurgischen Herstellung einer Turbinenschaufel bzw. eines einteiligen Turbinenlaufrads sowie zur Pulvervorbehandlung
DE2326284A1 (de) Werkstueck aus einer verdichteten superlegierung auf ni-basis
DE60008116T2 (de) Superlegierung mit optimiertem Hochtemperatur-Leistungsvermögen in Hochdruck-Turbinenscheiben
DE2401849A1 (de) Verfahren zum herstellen von verformten gegenstaenden aus einer dispersionsverfestigten legierung
EP1568486A1 (fr) Procédé de fabrication de demi-produits et pièces contenant des alliages d'aluminure de titane et produits ainsi obtenus
EP2990141A1 (fr) Procédé de fabrication de composants en Titanaluminide (TiAI)
EP3238863A1 (fr) Procédé de fabrication d'une aube de turbomachine
DE4434515C2 (de) Oxid-dispersionsverfestigte Legierung und daraus hergestellte Bauteile von Gasturbinen
DE102017215321A1 (de) Verfahren zur herstellung eines titanaluminid - bauteils mit zähem kern und entsprechend hergestelltes bauteil
EP0570072B1 (fr) Procédé d'obtention d'un alliage à base de chrome
AT392432B (de) Verfahren zur herstellung von warmkriechfesten halbfabrikaten oder formteilen aus hochschmelzenden metallen

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB IT LI NL

17P Request for examination filed

Effective date: 19940513

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17Q First examination report despatched

Effective date: 19970731

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ASEA BROWN BOVERI AG

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI NL

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 59308916

Country of ref document: DE

Date of ref document: 19981001

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19981027

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20010412

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20010418

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20010507

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20010509

Year of fee payment: 9

Ref country code: DE

Payment date: 20010509

Year of fee payment: 9

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

NLS Nl: assignments of ep-patents

Owner name: ALSTOM

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020521

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020531

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20021201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20021203

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20020521

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030131

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20021201

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050521