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EP1341945B1 - Procede de fabrication de composants en alliages tial a capacite de charge elevee - Google Patents

Procede de fabrication de composants en alliages tial a capacite de charge elevee Download PDF

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Publication number
EP1341945B1
EP1341945B1 EP01270635A EP01270635A EP1341945B1 EP 1341945 B1 EP1341945 B1 EP 1341945B1 EP 01270635 A EP01270635 A EP 01270635A EP 01270635 A EP01270635 A EP 01270635A EP 1341945 B1 EP1341945 B1 EP 1341945B1
Authority
EP
European Patent Office
Prior art keywords
components
deformation
phase domain
takes place
isothermic
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
EP01270635A
Other languages
German (de)
English (en)
Other versions
EP1341945A2 (fr
Inventor
Peter Janschek
Lothar Knippschild
Karl Schreiber
Dan Roth-Fagaraseanu
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.)
Rolls Royce Deutschland Ltd and Co KG
Leistritz AG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Leistritz AG
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
Priority claimed from DE10150674A external-priority patent/DE10150674B4/de
Application filed by Rolls Royce Deutschland Ltd and Co KG, Leistritz AG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1341945A2 publication Critical patent/EP1341945A2/fr
Application granted granted Critical
Publication of EP1341945B1 publication Critical patent/EP1341945B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Definitions

  • the invention relates to a method for producing high-strength components made of ⁇ + ⁇ -TiAl alloys, in particular of components for aircraft engines or stationary gas turbines.
  • TiAl-based alloys belong to the group of intermetallic materials which have been developed for applications in the area of the superalloy application temperature. With a density of about 4g / cm 3 , this new alloy class offers considerable potential for weight reduction and associated reduction of stresses on moving components at temperatures above 700 ° C. This weight and voltage reduction also has an effect on blades and disks of gas turbines or, for example, components of piston engines.
  • the difficulty of working TiAl alloys by forming processes is due to high yield stresses and low fracture toughness and ductility at low and medium temperatures. Forming processes must therefore be carried out at high temperatures in the region of the ⁇ + ⁇ or ⁇ -phase region in a protective atmosphere.
  • the US-A 5,593,282 discloses a rotor usable in engines, which may preferably be formed from a lightweight structural material, in this example a temperature resistant ceramic material or, alternatively, TiAl or NiAl materials.
  • a process for the production of shaped articles from titanium-aluminum-based alloys is described.
  • a cast blank with a lamellar structure with a lamella thickness of up to 1 ⁇ m is produced. This is deformed in the temperature range of 1050 ° C to 1300 ° C with a high degree of deformation, so that a dynamic recrystallization takes place with particle sizes up to 5 microns.
  • the blank is cooled and superplastic formed in the temperature range of 900 ° C to 1100 ° C at forming speeds of 10 -4 / s to 10 -1 / s to close to near-net shape moldings.
  • the mentioned very fine-grained microstructure is produced by the addition of silicon up to 0.3% by mass.
  • this silicon content leads to undesirable side effects, such as increased porosity and the formation of silicides, whereby the required mechanical strength is greatly impaired.
  • the fine-grained structure required for this superplastic forming is to be adjusted by extrusion, which does not lead to the finely crystalline equiaxial structure described elsewhere and required for superplastic forming.
  • the extent to which mechanical high-strength components can actually be produced by this process remains open, since in practice it has not yet been established.
  • the invention has for its object to provide a method for producing lightweight and heavy-duty components for conventional and air traffic engineering of TiAl alloys, with which over the prior art, improved fatigue strength, reliability and increased service life can be realized.
  • This object is achieved by a method for producing high-strength components from ⁇ + ⁇ -TiAl alloys, in particular components for aircraft engines or stationary gas turbines, by preforming encapsulated TiAl blanks of globular structure by isothermal primary deformation in the ⁇ + ⁇ or ⁇ -phase region, the preforms are formed by at least one isothermal secondary forming process under dynamic recrystallization in the ⁇ + ⁇ or ⁇ -phase region to components vorgebbarer contour and to adjust the microstructure, the components solution-annealed in the ⁇ -phase region and then cooled rapidly.
  • Very homogeneous TiAl blanks having a globular grain structure are used, which are subjected in a corresponding manner to primary and at least one subsequent secondary deformation in the ⁇ + ⁇ or ⁇ -phase region.
  • the primary forming can be done by forging or extrusion.
  • the secondary deformation is advantageously carried out by forging.
  • the forging blanks are encapsulated both in the primary and in the secondary forming, by which the expert can understand inter alia a forming tool with upper and lower part.
  • the suitable forging windows are characterized by a pronounced flow / stress maximum, which in contrast to the prior art according to DE-C 43 18 424 (Process window of superplasticity) stands. Characteristic of the forming process according to the invention is the dynamic recrystallization, which is associated with the high yield stress.
  • the components are solution-annealed in the ⁇ -phase region and then rapidly cooled. This rapid cooling from the ⁇ -phase region then leads to the desired fine-lamellar microstructure. Typical cooling rates are in the range of 10 ° C / s.
  • Silicon is not included in these alloys, since silicon is known to be the desired grain refinement, but on the other hand leads to the already mentioned undesirable accompanying effects, such as porosity and silicidation.
  • the isothermal deformation takes place advantageously in heated tools made of molybdenum or graphite.
  • the following example describes a method for producing rotor disks, which can be used for aircraft gas turbines, whereby other heavy-duty components than for the conventional and aviation technology, such as components of internal combustion engines (for example valves) may be addressed.
  • the blank is subjected in a first step to an isothermal primary forming at an ⁇ + ⁇ temperature of 1200 ° C.
  • a flat track system is used to generate so-called pancakes.
  • the isothermal primary deformation takes place at a deformation rate of 10 -4 / s.
  • the pancakes are forged in a shaping forging tool with upper and lower parts ready to slices.
  • the isothermal secondary deformation takes place in this example at an ⁇ + ⁇ temperature of 1150 ° C and a forming rate of 10 -3 / s instead.
  • the following example shows a method of making turbine blades usable in stationary gas turbines.
  • the first forging of a base material for ⁇ + ⁇ -TiAl blanks in this example take place in that in a forging die with a disk-shaped engraving, the volume distribution for a larger number of blanks (here 10 pieces) in the ⁇ + ⁇ phase region at about 1150 ° C is performed.
  • the separation of the blanks is to be brought about in this example in the high temperature range by a cutting tool. By this measure, a cooling of the blanks with subsequent reheating for the subsequent forming process is unnecessary.
  • the blanks are forged in a shaping forging tool with upper and lower parts to blades ready.
  • This secondary transformation takes place in this example in the ⁇ + ⁇ phase region at about 1150 ° C and a forming rate of 10 3 s -1 instead.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Compositions Of Oxide Ceramics (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)

Claims (8)

  1. Procédé pour la fabrication de composants à capacité de charge élevée à base d'alliages TiAl α+γ, en particulier de composants destinés à des groupes motopropulseurs ou des turbines à gaz fixes du fait que des ébauches en TiAl encapsulées de structure globulaire sont préformées par transformation primaire isotherme dans la zone de phase α+γ ou α, les préformes sont formées par au moins un processus de transformation secondaire isotherme avec recristallisation dynamique dans la zone de phase α+γ ou α en composants de contour prédéfinissable et les composants font l'objet d'un recuit de mise en solution dans la zone de phase α et d'un refroidissement rapide consécutif pour le réglage de la microstructure.
  2. Procédé selon la revendication 1, caractérisé en ce que la transformation primaire isotherme par forgeage ou extrusion a lieu dans la zone de phase α+γ dans une plage de températures allant de 1000° à 1340 °C.
  3. Procédé selon la revendication 1, caractérisé en ce que la transformation primaire isotherme par forgeage ou extrusion a lieu dans la zone de phase α entre 1340° et 1360 °C.
  4. Procédé selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la transformation secondaire isotherme a lieu dans la zone de phase α+γ dans la plage de températures entre 1000° et 1340 °C.
  5. Procédé selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le processus de transformation est effectué dans un outil en particulier chauffé à base de molybdène ou de graphite.
  6. Procédé selon l'une quelconque des revendications 1 à 5, caractérisé en ce que des ébauches à base d'un alliage de base Ti-Al de composition (en % d'atome) sont utilisées pour la transformation primaire et la transformation secondaire :
    43 % - 47 % Al
    5%-10%Nb
    maximum 1,0 % de B
    maximum 0,5 % de C
    le reste étant composé de titane et d'impuretés dues à fusion
  7. Procédé selon l'une quelconque des revendications 1 à 6, caractérisé en ce que le processus de recuit de transformation et le processus de recuit de mise en solution a lieu dans une atmosphère inerte.
  8. Procédé selon l'une quelconque des revendications 1 à 7, caractérisé en ce que le refroidissement pour le réglage terminal de la structure s'effectue à partir de la zone de phase α au-dessus de 1340 °C très rapidement, en particulier avec 10 °C/s - 20 °C/s dans de l'huile.
EP01270635A 2000-12-15 2001-11-16 Procede de fabrication de composants en alliages tial a capacite de charge elevee Expired - Lifetime EP1341945B1 (fr)

Applications Claiming Priority (9)

Application Number Priority Date Filing Date Title
DE10062776 2000-12-15
DE10062776 2000-12-15
DE10102497 2001-01-19
DE10102497 2001-01-19
DE10104639 2001-02-02
DE10104639 2001-02-02
DE10150674 2001-10-17
DE10150674A DE10150674B4 (de) 2000-12-15 2001-10-17 Verfahren zur Herstellung von hochbelastbaren Bauteilen aus TiAl-Legierungen
PCT/EP2001/013290 WO2002048420A2 (fr) 2000-12-15 2001-11-16 Procede de fabrication de composants en alliages tial a capacite de charge elevee

Publications (2)

Publication Number Publication Date
EP1341945A2 EP1341945A2 (fr) 2003-09-10
EP1341945B1 true EP1341945B1 (fr) 2008-01-09

Family

ID=27437912

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01270635A Expired - Lifetime EP1341945B1 (fr) 2000-12-15 2001-11-16 Procede de fabrication de composants en alliages tial a capacite de charge elevee

Country Status (7)

Country Link
US (1) US6997995B2 (fr)
EP (1) EP1341945B1 (fr)
JP (1) JP4259863B2 (fr)
AT (1) ATE383454T1 (fr)
AU (1) AU2002221859A1 (fr)
DE (1) DE50113483D1 (fr)
WO (1) WO2002048420A2 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6974507B2 (en) * 2003-03-03 2005-12-13 United Technologies Corporation Damage tolerant microstructure for lamellar alloys
US20090022982A1 (en) * 2006-03-06 2009-01-22 Tosoh Smd, Inc. Electronic Device, Method of Manufacture of Same and Sputtering Target
CN101395296B (zh) * 2006-03-06 2012-03-28 陶斯摩有限公司 溅射靶
DE102006037883B4 (de) * 2006-08-11 2008-07-31 Leistritz Ag Gesenk zum Hochtemperaturschmieden
DE102012201082B4 (de) 2012-01-25 2017-01-26 MTU Aero Engines AG Verfahren zur Herstellung geschmiedeter Bauteile aus einer TiAl-Legierung und entsprechend hergestelltes Bauteil
US9957836B2 (en) 2012-07-19 2018-05-01 Rti International Metals, Inc. Titanium alloy having good oxidation resistance and high strength at elevated temperatures
CN103801581B (zh) * 2014-01-24 2015-11-11 北京科技大学 一种高铌钛铝基合金板材的制备方法
DE102015103422B3 (de) * 2015-03-09 2016-07-14 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
DE102015115683A1 (de) * 2015-09-17 2017-03-23 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung einer Vorform aus einer Alpha+Gamma-Titanaluminid-Legierung zur Herstellung eines hochbelastbaren Bauteils für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
DE102018209881A1 (de) * 2018-06-19 2019-12-19 MTU Aero Engines AG Verfahren zur Herstellung eines geschmiedeten Bauteils aus einer TiAl-Legierung

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4294615A (en) * 1979-07-25 1981-10-13 United Technologies Corporation Titanium alloys of the TiAl type
JP2679109B2 (ja) * 1988-05-27 1997-11-19 住友金属工業株式会社 金属間化合物ＴｉＡ▲ｌ▼基軽量耐熱合金
CA2025272A1 (fr) * 1989-12-04 1991-06-05 Shyh-Chin Huang Alliages d'aluminure de titane a haute teneur en niobium
JP2728305B2 (ja) * 1989-12-25 1998-03-18 新日本製鐵株式会社 金属間化合物ＴｉＡ▲ｌ▼基合金の熱間加工法
JPH03193852A (ja) * 1989-12-25 1991-08-23 Nippon Steel Corp 超微細組織からなるＴｉＡｌ基合金の製造方法
US5082624A (en) * 1990-09-26 1992-01-21 General Electric Company Niobium containing titanium aluminide rendered castable by boron inoculations
US5489411A (en) * 1991-09-23 1996-02-06 Texas Instruments Incorporated Titanium metal foils and method of making
JPH05255827A (ja) * 1992-03-13 1993-10-05 Sumitomo Metal Ind Ltd ＴｉＡｌ金属間化合物基合金の製造方法
DE4318424C2 (de) * 1993-06-03 1997-04-24 Max Planck Inst Eisenforschung Verfahren zur Herstellung von Formkörpern aus Legierungen auf Titan-Aluminium-Basis
JP3489173B2 (ja) * 1994-02-01 2004-01-19 住友金属工業株式会社 Ｔｉ−Ａｌ系金属間化合物基合金の製造方法
AT2881U1 (de) * 1998-06-08 1999-06-25 Plansee Ag Verfahren zur herstellung eines tellerventiles aus gamma-tial-basislegierungen
USH1988H1 (en) * 1998-06-30 2001-09-04 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
US6174387B1 (en) * 1998-09-14 2001-01-16 Alliedsignal, Inc. Creep resistant gamma titanium aluminide alloy
DE10024343A1 (de) * 2000-05-17 2001-11-22 Gfe Met & Mat Gmbh Bauteil auf Basis von gamma-TiAl-Legierungen mit Bereichen mit gradiertem Gefüge
RU2203976C2 (ru) * 2001-06-13 2003-05-10 Институт проблем сверхпластичности металлов РАН СПОСОБ ОБРАБОТКИ ЛИТЫХ ЗАЭВТЕКТОИДНЫХ СПЛАВОВ НА ОСНОВЕ АЛЮМИНИДОВ ТИТАНА γ-TiAl И α-Ti3Al

Also Published As

Publication number Publication date
JP4259863B2 (ja) 2009-04-30
EP1341945A2 (fr) 2003-09-10
US20040094248A1 (en) 2004-05-20
DE50113483D1 (de) 2008-02-21
WO2002048420A2 (fr) 2002-06-20
US6997995B2 (en) 2006-02-14
JP2004538361A (ja) 2004-12-24
WO2002048420A3 (fr) 2002-08-08
AU2002221859A1 (en) 2002-06-24
ATE383454T1 (de) 2008-01-15

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