EP0574708A1 - Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément - Google Patents

Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément Download PDF

Info

Publication number
EP0574708A1
EP0574708A1 EP93107926A EP93107926A EP0574708A1 EP 0574708 A1 EP0574708 A1 EP 0574708A1 EP 93107926 A EP93107926 A EP 93107926A EP 93107926 A EP93107926 A EP 93107926A EP 0574708 A1 EP0574708 A1 EP 0574708A1
Authority
EP
European Patent Office
Prior art keywords
section
component
alloys
blade
press
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.)
Granted
Application number
EP93107926A
Other languages
German (de)
English (en)
Other versions
EP0574708B1 (fr
Inventor
Joachim Dr. Rösler
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.)
ABB Asea Brown Boveri Ltd
ABB AB
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 EP0574708A1 publication Critical patent/EP0574708A1/fr
Application granted granted Critical
Publication of EP0574708B1 publication Critical patent/EP0574708B1/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 a turbine blade, with a component body containing at least a first and a second section, in which the first section is formed from a ductile material and the second section is brittle compared to the ductile material Has material.
  • the invention is also based on a method for producing such a component.
  • the component described is designed as a turbine blade and is intended for use in a gas turbine. It has a blade body cast from a eutectic alloy and containing the blade root and blade blade.
  • the blade root is formed by a ductile cast body with a non-directional structure.
  • the airfoil consists of a matrix and parallel to each other and in Fibrous crystals aligned in the longitudinal direction of the blade, which are embedded in the matrix and which are formed by directional solidification from an inductively heated melt.
  • the blade is characterized by a significantly higher creep resistance with significantly reduced ductility. In particular when producing a large airfoil, however, it is difficult to achieve a temperature gradient which is sufficiently large for a directional solidification and thus the desired high creep resistance in the airfoil.
  • the invention is based on the object of specifying a component, in particular a turbine blade, of the type mentioned, which can be used in a device operated at medium and high temperatures, in particular a turbine , characterized by a long service life, and at the same time to point out a way that makes it possible to manufacture such a component in a simple and suitable for mass production.
  • the component according to the invention is distinguished from comparable components according to the prior art by a long service life. This is due, on the one hand, to the fact that sections of the component which are subjected to different loads, in particular which comprise a blade root or an airfoil, consist of differently specified alloys and are adapted to the different requirements. Since these alloys, which are matched to the graded graded properties of the component, such as the turbine blade in particular, contain a common base material, none occur in the border area of the sections chemical reaction products. The sections therefore merge into one another without a sharp transition, so that the component according to the invention can withstand the high thermal and mechanical loads that occur in graded fashion when a thermal machine, such as, in particular, a gas turbine or a compressor, are operated.
  • the process used to manufacture the components according to the invention is characterized in that even large components with high thermal and mechanical strength can be manufactured in a simple manner suitable for mass production by common process steps, such as in particular by hot isostatic pressing or by sintering.
  • FIGS. 1 and 2 and each designed as a turbine blade 1 each contain an elongate blade 2 and a blade root 3 formed on one end of the blade 2.
  • Reference number 4 denotes a press can.
  • this press can encloses the blade root 3 and has an opening 5 filled by the blade 2, which is preferably sealed gas-tight by welding or soldering the press can 4 to the blade 2.
  • the press can 4 encloses the entire turbine blade 1.
  • the turbine blade 1 shown in FIG. 1 is manufactured 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 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 4 receiving the blade root of the turbine blade 1 is filled with alloy powder.
  • the press can 4 is then evacuated and sealed gas-tight.
  • the materials for the cast body and the powder each contain one of two alloys of different chemical based on a common base material Compositions which differ from one another by the presence and / or the amount of at least one dopant alloyed into the base material.
  • An intermetallic phase in particular a gamma titanium aluminide, is preferably used as the base material.
  • At least one of the two alloys containing gamma-titanium aluminide has a proportion of at least 0.2 and at most 8 atomic percent of 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 for the airfoil 2 has, for example, the following composition: In atom%: 48 Al - 3 Cr - remainder Ti and impurities; In% by weight: 33.2 Al - 3.9 Cr - impurities less than 0.5 - balance Ti.
  • the size of the powder particles is typically less than 500 ⁇ m.
  • Another typical alloy for the airfoil has the following composition in atomic%: 48 Al - 2 Cr - 2 Ta - balance Ti and impurities.
  • a typical alloy for the blade root 3 has, for example, the following composition: In atom%: 48 Al - 2 Cr - 2 Nb - balance Ti and impurities; In% by weight: 32.5 Al - 2.9 Cr - 5 Nb - impurities less than 0.5 - balance Ti.
  • the size of the powder particles is typically less than 200 ⁇ m, preferably less than 100 ⁇ m.
  • Another typical alloy for the blade root has the following composition in atomic%: 48 Al - 2 Cr - 2 Ta - 0.5 Si - balance Ti and impurities.
  • the sample completed by gas-tight closing of the press can 4 is brought into a press device and compressed hot isostatically at temperatures between 900 and 1200 ° C.
  • a typical pressing process at approx. 1070 ° C took approx. 3 hours at a pressure of approx. 250 MPa.
  • the two alloys were compacted pore-free with a gradual transition from the airfoil 2 to the airfoil 3, without chemical reaction products being formed in the border area.
  • This composite material already having the shape of the turbine blade, was then typically heat-treated at temperatures above 700 ° C. for about 4 hours after removal of the deformed press can 4. Subsequently, the turbine blade according to the invention was completed by slight material-removing processing, such as grinding, polishing and / or electrochemical treatment.
  • a press can 4 which was extended in the longitudinal direction and accommodates the entire turbine blade 1 was used.
  • the cast body forming the airfoil 2 was first introduced into this press can 4 and the alloy powder was subsequently introduced in accordance with the exemplary embodiment described above.
  • the press can 4 was then evacuated and sealed gas-tight.
  • the test specimen produced in this way was treated in accordance with the exemplary embodiment described above.
  • the alloys used had the same composition as in the previously described embodiment.
  • a body made of a hot-isostatically compressed powder can also be introduced into the press can 4.
  • a further alternative embodiment of the invention that was used to form the airfoil Alloy powder with 48 atomic percent Al, 3 atomic percent Cr, the rest of Ti and small amounts of impurities at a temperature of approx. 1070 ° C and a pressure of approx. 250 MPa compressed hot isostatically for approx. 3 hours.
  • the resulting body was then brought into the press can 4 shown in FIG.
  • an alloy powder of the previously specified chemical composition forming the airfoil 2 was filled into the press can 4.
  • An alloy powder forming the blade root 3 was then backfilled with the composition specified in the previously described exemplary embodiments.
  • the press can 4 was then evacuated and sealed gas-tight without shaking and without mixing the filled powders with one another.
  • hot isostatic pressing for approx. 3 hours at approx. 1070 ° C and a pressure of approx. 250 MPa, a non-porous material was produced, from which after removing the press jug 4, after two hours of heat treatment at approx. 1350 ° C and post-processing to remove the material a turbine blade was manufactured according to the invention.
  • a turbine blade designed in this way can also be taken from FIG. 2 in accordance with the previously mentioned embodiment variants.
  • the micrograph according to FIG. 3 shows the structure and microstructure of a part indicated by a frame in FIG. 2 a turbine blade according to the invention, produced exclusively from alloy powders, as described above. It can be seen from this that the alloy forming the airfoil 2 has a coarse-grained microstructure and the alloy forming the airfoil 3 has a fine-grained microstructure, and that no undesired reaction zone with chemical reaction products or with precipitates occurs at the transition zone between the two alloys. Both alloys gradually merge into one another by interlocking coarse and fine crystallites.
  • the alloy forming the airfoil 2 has a ductility of approximately 0.5% at room temperature, while the alloy forming the airfoil 3 has a ductility of 2.1%.
  • the airfoil 2 has a creep resistance which, when corrected for density, is considerably higher than the creep resistance of the nickel-base superalloys usually used in this temperature range.
  • the entire turbine blade 1 shows a ductility of 0.5% corresponding to the material of the blade 2. Their mechanical and thermal properties are not affected by the transition zone between the two alloys.
  • 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 in the transition area is sufficiently high due to the common base material of the two alloys and the lack of brittle reaction products to ensure a safe To ensure operation of the turbine blade 1 at high temperatures.
  • the invention is not limited to turbine blades. It also relates to other components that are subjected to high mechanical loads at high temperatures, such as one-piece turbine wheels of turbochargers.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP93107926A 1992-06-13 1993-05-14 Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément Expired - Lifetime EP0574708B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4219470 1992-06-13
DE4219470A DE4219470A1 (de) 1992-06-13 1992-06-13 Bauteil für hohe Temperaturen, insbesondere Turbinenschaufel, und Verfahren zur Herstellung dieses Bauteils

Publications (2)

Publication Number Publication Date
EP0574708A1 true EP0574708A1 (fr) 1993-12-22
EP0574708B1 EP0574708B1 (fr) 1998-09-16

Family

ID=6461002

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93107926A Expired - Lifetime EP0574708B1 (fr) 1992-06-13 1993-05-14 Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément

Country Status (3)

Country Link
US (1) US5409781A (fr)
EP (1) EP0574708B1 (fr)
DE (2) DE4219470A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103790640A (zh) * 2014-02-19 2014-05-14 中国航空动力机械研究所 防轮盘爆裂叶片

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5768679A (en) * 1992-11-09 1998-06-16 Nhk Spring R & D Center Inc. Article made of a Ti-Al intermetallic compound
JP3839493B2 (ja) * 1992-11-09 2006-11-01 日本発条株式会社 Ｔｉ−Ａｌ系金属間化合物からなる部材の製造方法
DE19581384C2 (de) * 1994-10-25 1999-03-11 Mitsubishi Heavy Ind Ltd Auf einer intermetallischen Verbindung basierende Titan-Aluminium-Legierung
DE19756354B4 (de) 1997-12-18 2007-03-01 Alstom Schaufel und Verfahren zur Herstellung der Schaufel
DE19847222C2 (de) * 1998-10-13 2001-09-20 Asea Brown Boveri Turbinenschaufel für hohe mechanische und thermische Belastungen
US6699245B2 (en) 2001-02-05 2004-03-02 A-Med Systems, Inc. Anastomosis system and related methods
US20080066288A1 (en) * 2006-09-08 2008-03-20 General Electric Company Method for applying a high temperature anti-fretting wear coating
US9228445B2 (en) 2010-12-23 2016-01-05 General Electric Company Turbine airfoil components containing ceramic-based materials and processes therefor
US8721290B2 (en) * 2010-12-23 2014-05-13 General Electric Company Processes for producing components containing ceramic-based and metallic materials
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
GB201200360D0 (en) * 2012-01-11 2012-02-22 Rolls Royce Plc Component production method
WO2014093826A2 (fr) 2012-12-14 2014-06-19 United Technologies Corporation Coulage à multiples injections
EP3513889B1 (fr) 2012-12-14 2021-04-14 Raytheon Technologies Corporation Alliage et aube de turbine hybride pour une performance ou une architecture de moteur améliorée
US11066952B2 (en) * 2017-05-22 2021-07-20 Raytheon Technologies Corporation Green repair of oxidation and corrosion resistant coatings
US20190040749A1 (en) * 2017-08-01 2019-02-07 United Technologies Corporation Method of fabricating a turbine blade

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2317502A1 (fr) * 1975-06-27 1977-02-04 Special Metals Corp Roues composites a aubes, particulierement destinees aux turbines a gaz, et leur procede de fabrication
EP0073651A1 (fr) * 1981-08-27 1983-03-09 ASEA Stal Aktiebolag Procédé de fabrication d'éléments d'aubage pour turbomachines à fluide
US4529452A (en) * 1984-07-30 1985-07-16 United Technologies Corporation Process for fabricating multi-alloy components
US4787821A (en) * 1987-04-10 1988-11-29 Allied Signal Inc. Dual alloy rotor
US4825522A (en) * 1987-08-12 1989-05-02 Director General Of The Agency Of Industrial Science And Technology Method of making heat resistant heavy-duty components of a turbine by superplasticity forging wherein different alloys are junctioned
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
EP0513407A1 (fr) * 1991-05-13 1992-11-19 Asea Brown Boveri Ag Procédé de fabrication d' une aube de turbine

Family Cites Families (33)

* 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
US2946680A (en) * 1955-08-10 1960-07-26 Thompson Ramo Wooldridge Inc Powder metallurgy
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
CH602237A5 (fr) * 1974-12-23 1978-07-31 Bbc Brown Boveri & Cie
US3992200A (en) * 1975-04-07 1976-11-16 Crucible Inc. Method of hot pressing using a getter
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
DE2834222C3 (de) * 1978-08-04 1981-08-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verfahren zur Herstellung der Schaufel-Scheiben-Verbindung eines Turborotors
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
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
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
DE3241926A1 (de) * 1982-11-12 1984-05-17 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verbindung eines keramischen rotationsbauteils mit einem metallischen rotationsbauteil fuer stroemungsmaschinen, insbesondere gasturbinentriebwerke
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
US4851190A (en) * 1987-07-27 1989-07-25 Williams International Corporation Method of making a multi-alloy turbine rotor disk
US4900635A (en) * 1987-07-27 1990-02-13 Williams International Corporation Multi-alloy turbine rotor disk
US4808249A (en) * 1988-05-06 1989-02-28 The United States Of America As Represented By The Secretary Of The Air Force Method for making an integral titanium alloy article having at least two distinct microstructural regions
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.
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2317502A1 (fr) * 1975-06-27 1977-02-04 Special Metals Corp Roues composites a aubes, particulierement destinees aux turbines a gaz, et leur procede de fabrication
EP0073651A1 (fr) * 1981-08-27 1983-03-09 ASEA Stal Aktiebolag Procédé de fabrication d'éléments d'aubage pour turbomachines à fluide
US4529452A (en) * 1984-07-30 1985-07-16 United Technologies Corporation Process for fabricating multi-alloy components
US4787821A (en) * 1987-04-10 1988-11-29 Allied Signal Inc. Dual alloy rotor
US4825522A (en) * 1987-08-12 1989-05-02 Director General Of The Agency Of Industrial Science And Technology Method of making heat resistant heavy-duty components of a turbine by superplasticity forging wherein different alloys are junctioned
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
EP0513407A1 (fr) * 1991-05-13 1992-11-19 Asea Brown Boveri Ag Procédé de fabrication d' une aube de turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI Section Ch, Week 8433, Derwent Publications Ltd., London, GB; Class M27, AN 84-203979 & JP-A-59 116 360 (HITACHI) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103790640A (zh) * 2014-02-19 2014-05-14 中国航空动力机械研究所 防轮盘爆裂叶片
CN103790640B (zh) * 2014-02-19 2015-10-28 中国航空动力机械研究所 防轮盘爆裂叶片

Also Published As

Publication number Publication date
US5409781A (en) 1995-04-25
DE59308980D1 (de) 1998-10-22
DE4219470A1 (de) 1993-12-16
EP0574708B1 (fr) 1998-09-16

Similar Documents

Publication Publication Date Title
EP0574727B1 (fr) Méthode de production d'un élément réfractaire à partir de deux matériaux différents
EP0574708B1 (fr) Elément pour température élevée, en particulier aube de turbine et procédé de fabrication de cet élément
EP0513407B1 (fr) Procédé de fabrication d' une aube de turbine
DE2845792C2 (fr)
DE3780136T2 (de) Gesinterter verbundpresskoerper mit grosser haerte.
DE4440229C2 (de) Verfahren zum Herstellen von gegen Rißbildung widerstandsfähigen hochfesten Superlegierungsgegenständen
DE2927079C2 (fr)
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
DE2845834C2 (fr)
DE2542094A1 (de) Metallpulver, verfahren zur behandlung losen metallpulvers und verfahren zur herstellung eines verdichteten presslings
EP2990141B1 (fr) Procédé de fabrication de composants en Titanaluminide (TiAI)
DE2445462B2 (de) Verwendung einer Nickellegierung
EP3802898B1 (fr) Alliage de molybdène à densité optimisée
DE2326284A1 (de) Werkstueck aus einer verdichteten superlegierung auf ni-basis
DE69702949T2 (de) Kompositkarbidpulver zur Verwendung für Sinterkarbid und Verfahren zu dessen Herstellung
DE4434515C2 (de) Oxid-dispersionsverfestigte Legierung und daraus hergestellte Bauteile von Gasturbinen
AT392432B (de) Verfahren zur herstellung von warmkriechfesten halbfabrikaten oder formteilen aus hochschmelzenden metallen
DE2200670B2 (fr)
DE1558805C3 (de) Verfahren zur Herstellung von verformten Werkstücken aus dispersionsverstärkten Metallen oder Legierungen
DE2522636A1 (de) Verfahren zur herstellung eines im gefuege grobkoernigen koerpers aus einer superlegierung und nach dem verfahren hergestellter koerper
EP3015199A2 (fr) Procede de fabrication d'un alliage cible resistant a de hautes temperatures, dispositif, alliage et composant correspondant
DE4019305A1 (de) Pulver und produkte von tantal, niob und deren legierungen
DE3027287A1 (de) Quecksilber-freisetzende zusammensetzung und deren verwendung
DE19845376C5 (de) Hartmetall- oder Cermet-Körper

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): DE FR GB IT

17P Request for examination filed

Effective date: 19940513

17Q First examination report despatched

Effective date: 19970515

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

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

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REF Corresponds to:

Ref document number: 59308980

Country of ref document: DE

Date of ref document: 19981022

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

Effective date: 19981117

ET Fr: translation filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19990413

Year of fee payment: 7

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

Ref country code: FR

Payment date: 19990419

Year of fee payment: 7

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

Ref country code: DE

Payment date: 19990420

Year of fee payment: 7

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
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: 20000514

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

Effective date: 20000514

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: 20010131

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: 20010301

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: 20050514