EP0924308A1 - Intermetallische Legierungen auf Titan-Basis vom Ti2AlNb-Typ mit hoher Streckgrenze und guter Kriechbeständigkeit - Google Patents

Intermetallische Legierungen auf Titan-Basis vom Ti2AlNb-Typ mit hoher Streckgrenze und guter Kriechbeständigkeit Download PDF

Info

Publication number
EP0924308A1
EP0924308A1 EP98403187A EP98403187A EP0924308A1 EP 0924308 A1 EP0924308 A1 EP 0924308A1 EP 98403187 A EP98403187 A EP 98403187A EP 98403187 A EP98403187 A EP 98403187A EP 0924308 A1 EP0924308 A1 EP 0924308A1
Authority
EP
European Patent Office
Prior art keywords
temperature
hours
transus
heat treatment
minus
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
EP98403187A
Other languages
English (en)
French (fr)
Other versions
EP0924308B1 (de
Inventor
Thierry Eric Carisey
Ashok Kumar Gogia
Jean-Loup Strudel
Dipankar Banerjee
Alain Lasalmonie
Jean-Michel Franchet
Tapash Kumar Nandy
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.)
Etat Indien Chef Controleur De Recherche Et Deve
Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Safran Aircraft Engines SAS
Original Assignee
Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Etat Indien Chef Controleur De Recherche Et Developpement Drdo-Dmrl
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 Association pour la Recherche et le Developpement des Methodes et Processus Industriels, Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS, Etat Indien Chef Controleur De Recherche Et Developpement Drdo-Dmrl filed Critical Association pour la Recherche et le Developpement des Methodes et Processus Industriels
Publication of EP0924308A1 publication Critical patent/EP0924308A1/de
Application granted granted Critical
Publication of EP0924308B1 publication Critical patent/EP0924308B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • C22C27/02—Alloys based on vanadium, niobium, or tantalum

Definitions

  • the present invention relates to a family of titanium-based intermetallic alloys which combine a set of specific mechanical properties including a high yield strength, high creep resistance and sufficient ductility at room temperature.
  • Intermetallic alloys of the Ti 3 Al type have shown interesting specific mechanical characteristics. Ternary alloys with Nb additions have been tested in particular and their mechanical properties joined to a lower density than that of nickel-based alloys since between 4 and 5.5 depending on the Nb content, arouse great interest for aeronautical applications . These alloys also have a higher titanium fire resistance than the Ti-based alloys previously used in the construction of turbomachines.
  • the targeted applications relate to massive structural parts such as casings, massive rotating parts such as centrifugal impellers or as a matrix of composite materials for one-piece bladed rings.
  • the desired operating temperature ranges go up to 650 ° C or 700 ° C in the case of parts made of long fiber composite material.
  • US 4,292,077 and US 4,716,020 describe the results obtained by titanium-based intermetallic alloys containing 24 to 27 Al and 11 to 16 Nb in percentages atomic.
  • the present invention relates to a family of titanium-based intermetallic alloys avoiding the drawbacks of the aforementioned known solutions and which are characterized by a chemical composition, in atomic percentages, belonging to the following field: A116-26; Num 18-28; Mo 0 to 2; If O to 0.8; Ta O at 2; Zr O at 2 and Ti complement at 100 with the condition Mo + Si + Zr + Ta> 0.4%.
  • thermomechanical treatments and a method of are further defined for these alloys intermetallic according to the invention, allowing improve their mechanical properties, in particular increase ductility at room temperature and limit plastic deformation during primary creep.
  • Tantalum is a ⁇ -gene element very similar to niobium to which it is often mixed in ores. In the titanium alloys it increases their mechanical strength and gives them better resistance to corrosion and oxidation.
  • Zirconium is a neutral element and the methods of alloys and the origin of the elements brought, by recycling or not, can bring the presence of Zr, which may in some cases be desired.
  • the atomic percentage used for the alloys of the invention for Zr, as for Ta, is is between 0 and 2%.
  • a process for developing the material has also been developed. point in accordance with the invention and makes it possible to obtain the mechanical properties sought and previously described.
  • the first step consists in homogenizing the composition of the material, using for example the VAR process (Vacuum Arc Remelting), this step is important because it determines the homogeneity of the material.
  • the material is then deformed at high speed to reduce the grain size either by forging with a pestle in the ⁇ domain, or by high speed extrusion still in the ⁇ domain. These bars are then cut into pieces to undergo the last stage of the thermomechanical treatment: isothermal forging. This isothermal forging takes place in a temperature range from T ⁇ -125 ° C to T ⁇ -25 ° C and with deformation rates from 5.10 -4 s -1 to 5.10 -2 s. -1 .
  • T ⁇ is the transition temperature between the high-temperature single-phase ⁇ domain and the two-phase domain ⁇ 2 + B 2
  • ⁇ 2 is a phase of defined composition Ti3Al transforming into phase 0 below about 900 ° C.
  • T ⁇ is around 1065 ° C for example, for a Ti 22 Al 25 Nb alloy.
  • the bars obtained by forging or extrusion can, as a variant, be subjected to a rolling operation where the deformation rates are of the order of 10 ⁇ 1 s ⁇ 1 .
  • the preparation of the material ends with a heat treatment which consists of three stages.
  • the first step is a step of re-solution at a temperature between T ⁇ -35 ° C and T ⁇ + 15 ° C for less than 2 hours.
  • the second stage allows the growth of the hardening phase O and this aging is carried out between 750 ° C and 950 ° C for at least 16 hours.
  • the third treatment is carried out within a range of temperature of 100 ° C around the operating temperature of the material.
  • the heat treatment in the vicinity of the temperature of the transition T ⁇ causes the recrystallization of the grains B2 and makes it possible to significantly increase the creep resistance at 650 ° C.
  • this treatment reduces the elastic limit, but increases the ductility around 350 ° C.
  • a heat treatment at a temperature further (-25 ° C) from that of the T ⁇ transition increases the elastic limit and increases the creep resistance at 550 ° C.
  • this treatment achieves a ductility plateau around 10% from 200 ° C to 600 ° C.
  • Intermetallic alloy samples including the composition belongs to the field of the invention have been tested and showed improvements in results compared to the prior known alloy of standard composition Ti 22Al 25Nb.
  • thermomechanical treatment is characterized by low temperature forging T ⁇ -100 ° C and heat treatment at T ⁇ -25 ° C before a 24 hour plateau at 900 ° C and aging at 550 ° C for at least 2 days.
  • the compression creep tests in these two examples also show the interest of the elements Ta and Zr for increase the creep resistance by decreasing the amplitude of the primary creep and reduction of the speed of secondary creep.
  • the results are shown in the figure 10 for compression creep tests at 650 ° C under 310MPa, on curve 5 for the Ti-24 Al-20Nb alloy, on the curve 6 for the Ti-24Al-20Nb-1Ta alloy and curve 7 for Ti-24Al-20Nb-1Zr alloy.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98403187A 1997-12-18 1998-12-17 Intermetallische Legierungen auf Titan-Basis vom Ti2AlNb-Typ mit hoher Streckgrenze und guter Kriechbeständigkeit Expired - Lifetime EP0924308B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9716057 1997-12-18
FR9716057A FR2772790B1 (fr) 1997-12-18 1997-12-18 ALLIAGES INTERMETALLIQUES A BASE DE TITANE DU TYPE Ti2AlNb A HAUTE LIMITE D'ELASTICITE ET FORTE RESISTANCE AU FLUAGE

Publications (2)

Publication Number Publication Date
EP0924308A1 true EP0924308A1 (de) 1999-06-23
EP0924308B1 EP0924308B1 (de) 2002-05-02

Family

ID=9514764

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98403187A Expired - Lifetime EP0924308B1 (de) 1997-12-18 1998-12-17 Intermetallische Legierungen auf Titan-Basis vom Ti2AlNb-Typ mit hoher Streckgrenze und guter Kriechbeständigkeit

Country Status (5)

Country Link
US (1) US6132526A (de)
EP (1) EP0924308B1 (de)
JP (1) JP4004163B2 (de)
DE (1) DE69805148T2 (de)
FR (1) FR2772790B1 (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2210612C2 (ru) * 2001-09-24 2003-08-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Сплав на основе титана и изделие, выполненное из него
FR2979702A1 (fr) * 2011-09-05 2013-03-08 Snecma Procede de preparation d'eprouvettes de caracterisation mecanique d'un alliage de titane
CN103710554A (zh) * 2014-01-23 2014-04-09 哈尔滨工业大学 一种用真空压力浸渗法制备Ti2AlNb合金的方法
CN104233141A (zh) * 2013-06-06 2014-12-24 中国科学院金属研究所 一种Ti2AlNb基合金电子束焊接后消除应力的退火热处理工艺
CN104357804A (zh) * 2014-10-14 2015-02-18 南京航空航天大学 Ti2AlNb合金表面抗高温氧化复合梯度涂层及其制备方法
FR3030577A1 (fr) * 2014-12-22 2016-06-24 Snecma Alliage intermetallique a base de titane
CN104357804B (zh) * 2014-10-14 2017-01-04 南京航空航天大学 Ti2AlNb合金表面抗高温氧化复合梯度涂层及其制备方法
CN106637013A (zh) * 2016-10-28 2017-05-10 机械科学研究总院先进制造技术研究中心 一种提高Ti2AlNb基合金高温强度的热处理方法
CN106914508A (zh) * 2017-02-17 2017-07-04 中国航空工业集团公司北京航空材料研究院 一种Ti2AlNb合金丝材的制备方法
CN111394637A (zh) * 2020-04-17 2020-07-10 中国航发北京航空材料研究院 一种Ti2AlNb合金及其棒材的制备方法
CN113462997A (zh) * 2021-06-30 2021-10-01 中国航发动力股份有限公司 一种电子束焊后提高焊缝性能的热处理方法
CN115612879A (zh) * 2022-09-13 2023-01-17 南昌航空大学 一种含Ta元素的Ti2AlNb合金及其制备方法
CN121447045A (zh) * 2026-01-06 2026-02-03 昱华先进材料科技(陕西)有限公司 一种Ti2AlNb基合金环件及其制备方法和应用

Families Citing this family (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3774758B2 (ja) * 2000-06-26 2006-05-17 独立行政法人物質・材料研究機構 ＴｉＢ粒子強化Ｔｉ２ＡｌＮｂ金属間化合物基複合材料とその製造方法
US6436208B1 (en) 2001-04-19 2002-08-20 The United States Of America As Represented By The Secretary Of The Navy Process for preparing aligned in-situ two phase single crystal composites of titanium-niobium alloys
US20040221929A1 (en) 2003-05-09 2004-11-11 Hebda John J. Processing of titanium-aluminum-vanadium alloys and products made thereby
US7837812B2 (en) 2004-05-21 2010-11-23 Ati Properties, Inc. Metastable beta-titanium alloys and methods of processing the same by direct aging
US8337750B2 (en) 2005-09-13 2012-12-25 Ati Properties, Inc. Titanium alloys including increased oxygen content and exhibiting improved mechanical properties
US7611592B2 (en) * 2006-02-23 2009-11-03 Ati Properties, Inc. Methods of beta processing titanium alloys
US10053758B2 (en) 2010-01-22 2018-08-21 Ati Properties Llc Production of high strength titanium
US9255316B2 (en) 2010-07-19 2016-02-09 Ati Properties, Inc. Processing of α+β titanium alloys
US8499605B2 (en) 2010-07-28 2013-08-06 Ati Properties, Inc. Hot stretch straightening of high strength α/β processed titanium
US9206497B2 (en) 2010-09-15 2015-12-08 Ati Properties, Inc. Methods for processing titanium alloys
US8613818B2 (en) 2010-09-15 2013-12-24 Ati Properties, Inc. Processing routes for titanium and titanium alloys
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
US8652400B2 (en) 2011-06-01 2014-02-18 Ati Properties, Inc. Thermo-mechanical processing of nickel-base alloys
US9050647B2 (en) 2013-03-15 2015-06-09 Ati Properties, Inc. Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys
CN104001845B (zh) * 2013-02-25 2017-04-12 钢铁研究总院 一种Ti2AlNb合金大尺寸盘件的锻造工艺方法
US9869003B2 (en) 2013-02-26 2018-01-16 Ati Properties Llc Methods for processing alloys
US9192981B2 (en) 2013-03-11 2015-11-24 Ati Properties, Inc. Thermomechanical processing of high strength non-magnetic corrosion resistant material
US9777361B2 (en) 2013-03-15 2017-10-03 Ati Properties Llc Thermomechanical processing of alpha-beta titanium alloys
US11111552B2 (en) 2013-11-12 2021-09-07 Ati Properties Llc Methods for processing metal alloys
CN104148562B (zh) * 2014-06-30 2017-01-11 贵州安大航空锻造有限责任公司 Ti2AlNb基合金铸锭的开坯方法
CN104372202A (zh) * 2014-11-25 2015-02-25 西北有色金属研究院 一种低密度高塑性Ti2AlNb合金
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
RU2586947C1 (ru) * 2015-06-25 2016-06-10 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Сплав на основе титана и изделие, выполненное из него
CN105331849B (zh) * 2015-10-10 2017-04-26 中国航空工业集团公司北京航空材料研究院 一种Ti2AlNb基合金
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys
RU2644830C2 (ru) * 2015-12-17 2018-02-14 Акционерное Общество "Чепецкий Механический Завод" (Ао Чмз) Способ изготовления прутковых заготовок из сплавов на основе интерметаллида титана с орто-фазой
CN105695799B (zh) * 2016-04-06 2017-12-15 中国航空工业集团公司北京航空材料研究院 一种Ti‑Al‑Nb系金属间化合物高温结构材料
CN105665729A (zh) * 2016-04-11 2016-06-15 西安欧中材料科技有限公司 一种高致密Ti2AlNb粉末合金近净成形工艺
US20170306467A1 (en) * 2016-04-22 2017-10-26 Arconic Inc. Methods for finishing extruded titanium products
RU2635204C1 (ru) * 2016-12-29 2017-11-09 федеральное государственное автономное образовательное учреждение высшего образования "Санкт-Петербургский политехнический университет Петра Великого" (ФГАОУ ВО "СПбПУ") Способ получения интерметаллидного ортосплава на основе титана
RU2656626C1 (ru) * 2017-05-15 2018-06-06 Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) Способ получения проволоки из сплава титан-ниобий-тантал-цирконий с эффектом памяти формы
CN108465819B (zh) * 2018-03-14 2020-04-03 燕山大学 Ti-22Al-25Nb(at.％)固溶体的机械合金化制备方法
RU2694099C1 (ru) * 2018-10-22 2019-07-09 Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) Способ изготовления тонкой проволоки из биосовместимого сплава TiNbTaZr
CN109332693A (zh) * 2018-11-08 2019-02-15 有研工程技术研究院有限公司 一种激光增材制造的三相Ti2AlNb基合金的热处理工艺
CN111647771B (zh) * 2020-04-17 2021-10-15 中国航发北京航空材料研究院 一种多元素复合抗氧化Ti2AlNb合金及其制备方法
CN113684383B (zh) * 2020-05-19 2022-10-18 宝武特种冶金有限公司 一种大规格高Nb-TiAl合金铸锭的制备方法
RU2751065C1 (ru) * 2020-08-06 2021-07-07 Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) Способ получения проволоки из сплава титан-ниобий-тантал для применения в производстве сферического порошка
CN112247043B (zh) * 2020-08-28 2022-04-12 中国科学院金属研究所 一种Ti2AlNb基合金锻件的制备工艺
CN112410698B (zh) * 2020-11-03 2021-11-02 中国航发北京航空材料研究院 一种三相Ti2AlNb合金多层次组织均匀性控制方法
RU2759624C1 (ru) * 2020-12-25 2021-11-16 Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) Способ получения тонкой проволоки из сплава TiNiTa
CN113862515B (zh) * 2021-09-30 2022-04-19 中国航发北京航空材料研究院 一种复合合金化Ti2AlNb合金多重强化热处理方法
US12344918B2 (en) 2023-07-12 2025-07-01 Ati Properties Llc Titanium alloys
CN116987991B (zh) * 2023-09-26 2024-01-23 成都先进金属材料产业技术研究院股份有限公司 一种调控Ti2AlNb基合金屈强比的方法
CN117403098B (zh) * 2023-09-27 2026-04-03 中国航发北京航空材料研究院 一种高热强性能Ti2AlNb合金及其热机械处理方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0388527A1 (de) * 1989-03-20 1990-09-26 General Electric Company Titanaluminid-Legierungen
EP0464366A1 (de) * 1990-07-04 1992-01-08 Asea Brown Boveri Ag Verfahren zur Herstellung eines Werkstücks aus einer dotierstoffhaltigen Legierung auf der Basis Titanaluminid
WO1992009713A1 (fr) * 1990-11-26 1992-06-11 Office National D'etudes Et De Recherches Aerospatiales Alliages et composes intermetalliques a base de niobium ou de tantale a haute resistance specifique
FR2674257A1 (fr) * 1991-03-20 1992-09-25 Armines Alliages a base de niobium et de titane resistant a l'oxydation a hautes temperatures.
EP0539152A1 (de) * 1991-10-21 1993-04-28 General Electric Company Niob enthaltende Titanaluminidlegierungen
US5442847A (en) * 1994-05-31 1995-08-22 Rockwell International Corporation Method for thermomechanical processing of ingot metallurgy near gamma titanium aluminides to refine grain size and optimize mechanical properties

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5417779A (en) * 1988-09-01 1995-05-23 United Technologies Corporation High ductility processing for alpha-two titanium materials
US5447582A (en) * 1993-12-23 1995-09-05 The United States Of America As Represented By The Secretary Of The Air Force Method to refine the microstructure of α-2 titanium aluminide-based cast and ingot metallurgy articles
AU705336B2 (en) * 1994-10-14 1999-05-20 Osteonics Corp. Low modulus, biocompatible titanium base alloys for medical devices
JPH08283890A (ja) * 1995-04-13 1996-10-29 Nippon Steel Corp 耐クリープ特性に優れたＴｉＡｌ基金属間化合物とその製造方法
JPH0931558A (ja) * 1995-07-19 1997-02-04 Daido Steel Co Ltd 真空アーク再溶解法
JP3303641B2 (ja) * 1995-12-15 2002-07-22 住友金属工業株式会社 耐熱チタン合金

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0388527A1 (de) * 1989-03-20 1990-09-26 General Electric Company Titanaluminid-Legierungen
EP0464366A1 (de) * 1990-07-04 1992-01-08 Asea Brown Boveri Ag Verfahren zur Herstellung eines Werkstücks aus einer dotierstoffhaltigen Legierung auf der Basis Titanaluminid
WO1992009713A1 (fr) * 1990-11-26 1992-06-11 Office National D'etudes Et De Recherches Aerospatiales Alliages et composes intermetalliques a base de niobium ou de tantale a haute resistance specifique
FR2674257A1 (fr) * 1991-03-20 1992-09-25 Armines Alliages a base de niobium et de titane resistant a l'oxydation a hautes temperatures.
EP0539152A1 (de) * 1991-10-21 1993-04-28 General Electric Company Niob enthaltende Titanaluminidlegierungen
US5442847A (en) * 1994-05-31 1995-08-22 Rockwell International Corporation Method for thermomechanical processing of ingot metallurgy near gamma titanium aluminides to refine grain size and optimize mechanical properties

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2210612C2 (ru) * 2001-09-24 2003-08-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Сплав на основе титана и изделие, выполненное из него
FR2979702A1 (fr) * 2011-09-05 2013-03-08 Snecma Procede de preparation d'eprouvettes de caracterisation mecanique d'un alliage de titane
WO2013034851A1 (fr) * 2011-09-05 2013-03-14 Snecma Procédé de préparation d'éprouvettes de caractérisation mécanique d'un alliage de titane
CN104233141A (zh) * 2013-06-06 2014-12-24 中国科学院金属研究所 一种Ti2AlNb基合金电子束焊接后消除应力的退火热处理工艺
CN103710554A (zh) * 2014-01-23 2014-04-09 哈尔滨工业大学 一种用真空压力浸渗法制备Ti2AlNb合金的方法
CN103710554B (zh) * 2014-01-23 2015-10-28 哈尔滨工业大学 一种用真空压力浸渗法制备Ti2AlNb合金的方法
CN104357804A (zh) * 2014-10-14 2015-02-18 南京航空航天大学 Ti2AlNb合金表面抗高温氧化复合梯度涂层及其制备方法
CN104357804B (zh) * 2014-10-14 2017-01-04 南京航空航天大学 Ti2AlNb合金表面抗高温氧化复合梯度涂层及其制备方法
US10119180B2 (en) 2014-12-22 2018-11-06 Safran Aircraft Engines Titanium-based intermetallic alloy
FR3030577A1 (fr) * 2014-12-22 2016-06-24 Snecma Alliage intermetallique a base de titane
WO2016102806A1 (fr) * 2014-12-22 2016-06-30 Snecma Alliage intermétallique à base de titane
CN106637013A (zh) * 2016-10-28 2017-05-10 机械科学研究总院先进制造技术研究中心 一种提高Ti2AlNb基合金高温强度的热处理方法
CN106637013B (zh) * 2016-10-28 2018-06-08 北京机科国创轻量化科学研究院有限公司 一种提高Ti2AlNb基合金高温强度的热处理方法
CN106914508B (zh) * 2017-02-17 2018-05-29 中国航空工业集团公司北京航空材料研究院 一种Ti2AlNb合金丝材的制备方法
CN106914508A (zh) * 2017-02-17 2017-07-04 中国航空工业集团公司北京航空材料研究院 一种Ti2AlNb合金丝材的制备方法
CN111394637A (zh) * 2020-04-17 2020-07-10 中国航发北京航空材料研究院 一种Ti2AlNb合金及其棒材的制备方法
CN111394637B (zh) * 2020-04-17 2021-06-01 中国航发北京航空材料研究院 一种Ti2AlNb合金及其棒材的制备方法
CN113462997A (zh) * 2021-06-30 2021-10-01 中国航发动力股份有限公司 一种电子束焊后提高焊缝性能的热处理方法
CN113462997B (zh) * 2021-06-30 2022-08-02 中国航发动力股份有限公司 一种电子束焊后提高焊缝性能的热处理方法
CN115612879A (zh) * 2022-09-13 2023-01-17 南昌航空大学 一种含Ta元素的Ti2AlNb合金及其制备方法
CN121447045A (zh) * 2026-01-06 2026-02-03 昱华先进材料科技(陕西)有限公司 一种Ti2AlNb基合金环件及其制备方法和应用

Also Published As

Publication number Publication date
DE69805148T2 (de) 2002-12-12
US6132526A (en) 2000-10-17
DE69805148D1 (de) 2002-06-06
JPH11241131A (ja) 1999-09-07
JP4004163B2 (ja) 2007-11-07
FR2772790A1 (fr) 1999-06-25
EP0924308B1 (de) 2002-05-02
FR2772790B1 (fr) 2000-02-04

Similar Documents

Publication Publication Date Title
EP0924308B1 (de) Intermetallische Legierungen auf Titan-Basis vom Ti2AlNb-Typ mit hoher Streckgrenze und guter Kriechbeständigkeit
EP0863219B1 (de) Titanaluminid zum Gebrauch bei erhöhter Temperatur
CA2583140C (fr) Alliage a base de nickel
FR2554130A1 (fr) Procede de traitement d'alliages de titane
FR2941962A1 (fr) Procede de fabrication d'une piece en superalliage a base de nickel, et piece ainsi obtenue.
JPH03170632A (ja) ニッケル基超合金及びその製法
FR2853666A1 (fr) ALLIAGE Al-Zn A HAUTE RESISTANCE,PROCEDE DE PRODUCTION DE PRODUITS EN UN TEL ALLIAGE, ET PRODUITS OBTENUS SELON CE PROCEDE
FR2949235A1 (fr) Superalliage base nickel et pieces realisees en ce superalliage
EP0864664A1 (de) Verfahren zur Herstellung eines superelastischen Artikels aus Nickel-Titan-Legierung
EP1544315B1 (de) Knetprodukt in Form eines gewalzten Bleches und Strukturbauteil für Flugzeug aus Al-Zn-Cu-Mg-Legierung
WO2010023405A2 (fr) Procédé de préparation d'une pièce en superalliage base nickel et pièce ainsi obtenue
CN102223964A (zh) 通过初始β锻制造钛零件的方法
FR2624882A1 (fr) Procede de revetement de pieces en alliages de titane par de l'aluminium diffuse
FR2633942A1 (fr) Superalliage a base de nickel resistant aux pendillements par fatigue et son procede de fabrication
FR3030577B1 (fr) Alliage intermetallique a base de titane
EP3117017B1 (de) Ausscheidungshärtende nickellegierung, aus besagter legierung hergestelltes teil und herstellungsverfahren dafür
EP0792945B1 (de) Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis
EP0758684B1 (de) Superlegierungen auf Nickelbasis mit gute Hochtemperatursbeständigkeit
FR2655353A1 (fr) Alliage d'aluminure de titane a forte teneur en niobium et produit obtenu a partir d'un tel alliage.
EP0194925B1 (de) Einkristalline Legierung mit Matrix auf Nickelbasis
FR2628349A1 (fr) Procede de forgeage de pieces en superalliage a base de nickel
EP1584697B1 (de) Titan-Aluminium-Legierung mit ausgezeichneter Dehnbarkeit bei hohen Temperaturen
EP4575027A1 (de) Legierung aus cunisn mit spiodaler entmischung und herstellungsverfahren davon
BE516044A (de)
CH322347A (fr) Alliage et utilisation de cet alliage

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

17P Request for examination filed

Effective date: 19990112

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

AKX Designation fees paid

Free format text: DE FR GB

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17Q First examination report despatched

Effective date: 20010727

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Owner name: ASSOCIATION POUR LA RECHERCHE ET LE DEVELOPPEMENT

Owner name: ETAT INDIEN, CHEF CONTROLEUR DE RECHERCHE ET DEVE

Owner name: SNECMA MOTEURS

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 69805148

Country of ref document: DE

Date of ref document: 20020606

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

Effective date: 20020720

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

Effective date: 20030204

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170717

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

Ref country code: DE

Payment date: 20171120

Year of fee payment: 20

Ref country code: FR

Payment date: 20171121

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20171121

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69805148

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20181216

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 EXPIRATION OF PROTECTION

Effective date: 20181216