EP1507017A1 - Procédé pour le traitement thermique des alliages de TiAl - Google Patents

Procédé pour le traitement thermique des alliages de TiAl Download PDF

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Publication number
EP1507017A1
EP1507017A1 EP04254344A EP04254344A EP1507017A1 EP 1507017 A1 EP1507017 A1 EP 1507017A1 EP 04254344 A EP04254344 A EP 04254344A EP 04254344 A EP04254344 A EP 04254344A EP 1507017 A1 EP1507017 A1 EP 1507017A1
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EP
European Patent Office
Prior art keywords
titanium aluminide
temperature
aluminide alloy
alpha
titanium
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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.)
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EP04254344A
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German (de)
English (en)
Inventor
Dawei Hu
Xinhua Wu
Michael Loretto
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1507017A1 publication Critical patent/EP1507017A1/fr
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    • 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 present invention relates to a method of heat-treating titanium aluminide and in particular to a method of heat-treating gamma titanium aluminide.
  • Our European patent application no. 03253539.5 filed 4 June 2003 discloses a method of heat-treating a titanium aluminide alloy having a single alpha phase field and being capable of producing a massively transformed gamma microstructure.
  • a method of heat-treating the titanium aluminide alloy is heated to a temperature above the alpha transus temperature, is maintained above the alpha transus temperature in the single alpha phase field for a predetermined time period, is cooled from the single alpha phase field to ambient temperature to produce a massively transformed gamma microstructure, is heated to a temperature below the alpha transus temperature in the alpha and gamma phase field, is maintained at the temperature below the alpha transus temperature for a predetermined time period to precipitate alpha plates in the massively transformed gamma microstructure such that a refined microstructure is produced and is then cooled to ambient temperature.
  • a problem with this heat-treatment is that the cooling, quenching, of the titanium aluminide from above the alpha transus to ambient temperature induces quenching stresses in the titanium aluminide.
  • a further problem is that the heat-treatment is only suitable for relatively thin castings.
  • Another problem is that the heat-treatment is only applicable to compositions of titanium aluminide with a particular range of aluminium.
  • the present invention seeks to provide a novel method of heat-treating titanium aluminide alloy which reduces, preferably overcomes, the above-mentioned problems.
  • the present invention provides a method of heat-treating titanium aluminide alloy, the titanium aluminide alloy having a single alpha phase field and being capable of producing a massively transformed gamma microstructure, the method comprising the steps of :-
  • the predetermined time period is up to 2 hours.
  • the predetermined time period is up to 4 hours.
  • step (e) comprises heating the titanium aluminide alloy to a temperature about 30°C to 60°C below the alpha transus temperature.
  • step (a) comprises heating the titanium aluminide alloy to a temperature of about 20°C to 30°C above the alpha transus temperature.
  • step (g) comprises air-cooling or furnace cooling.
  • step (c) comprises fluidised bed cooling or salt bath cooling.
  • titanium aluminide may be cooled to ambient temperature by air-cooling or oil cooling
  • the titanium aluminide alloy may comprise 48at% aluminium, 2at% chromium, 2at% niobium and the balance titanium and incidental impurities.
  • the alpha transus temperature is about 1360°C
  • step (a) comprises heating to a temperature of 1380°C
  • step (b) comprises maintaining the titanium aluminide alloy at a temperature of about 1380°C for about 1 hour
  • step (c) and (d) comprise salt bath, or fluidised bed, cooling the titanium aluminide alloy from a temperature of 1380°C to a temperature between 900°C and 1200°C and maintaining the titanium aluminide alloy at the temperature in the range of 900°C to 1200°C for a predetermined time period to produce a massively transformed gamma microstructure
  • steps (e) and (f) comprise heating the titanium aluminide alloy to a temperature of about 1320°C for about 2 hours to precipitate alpha plates in the massively transformed gamma microstructure such that a refined microstructure is produced in the titanium aluminide alloy
  • step (g) comprises air cooling the titanium aluminide alloy to ambient temperature.
  • the titanium aluminide alloy may comprise 46at% aluminium, 8at% niobium, up to 0.07at% carbon and the balance titanium and incidental impurities.
  • the alpha transus temperature is about 1335°C
  • step (a) comprises heating to a temperature of 1360°C
  • step (b) comprises maintaining the titanium aluminide alloy at a temperature of about 1360°C for about 1 hour
  • steps (c) and (d) comprise salt bath cooling, or fluidised bed cooling, the titanium aluminide alloy from a temperature of 1360°C to a temperature between 900°C and 1200°C and maintaining the titanium aluminide alloy at the temperature in the range of 900°C to 1200°C for a predetermined time period to produce a massively transformed gamma microstructure
  • steps (e) and (f) comprise heating the titanium aluminide alloy to a temperature of about 1300°C to about 1320°C for about 4 hours to precipitate alpha plates in the massively transformed gamma microstructure such that a refined microstructure is produced in the titanium aluminide alloy
  • step (g) comprises air cooling the titanium aluminide alloy to ambient temperature.
  • the titanium aluminide alloy may consist of 45-46at% aluminium, 8at% niobium, up to 0.07at% carbon and the balance is titanium and incidental impurities.
  • the titanium aluminide alloy may consist of 45-46at% aluminium, 2-6at% niobium, 2-6at% hafnium and the balance is titanium plus incidental impurities.
  • the titanium aluminide alloy may be a cast titanium aluminide component.
  • the method may comprise hot isostatic pressing of the cast titanium aluminide alloy component.
  • step (f) Preferably the hot isostatic pressing of the cast titanium aluminide alloy component is concurrent with step (f).
  • the hot isostatic pressing comprises applying a pressure of about 150MPa for about 4 hours.
  • the titanium aluminide alloy may be a compressor blade or a compressor vane.
  • a method of heat-treating a titanium aluminide alloy according to the present invention is described with reference to figure 1.
  • the present invention is concerned with heat-treating gamma titanium aluminide alloys with at least 46at% aluminium and a single alpha phase field.
  • the heat treatment process comprises heating the gamma titanium aluminide to a temperature T 1 above the alpha transus temperature T ⁇ .
  • the gamma titanium aluminide alloy is then maintained at a temperature T 1 above the alpha transus temperature T ⁇ in the single alpha phase field for a predetermined time period t 1 .
  • the gamma titanium aluminide is quenched, for example fluidised bed cooled, or slat bath cooled, from the single alpha phase field at temperature T 1 to a temperature T 2 .
  • the gamma titanium aluminide alloy is maintained at temperature T 2 for a predetermined time period t 2 to produce a massively transformed gamma microstructure.
  • the gamma titanium aluminide alloy is then heated to a temperature T 3 below the alpha transus temperature T ⁇ .
  • the gamma titanium aluminide alloy is maintained at the temperature T 3 in the alpha and gamma phase field for a predetermined time period t 3 to precipitate alpha plates in the massively transformed gamma microstructure such that a refined microstructure is produced in the titanium aluminide alloy.
  • the gamma titanium aluminide is cooled, for example air cooled, or furnace cooled, to ambient temperature.
  • the gamma titanium aluminide is heated to a temperature T 1 about 20°C to 30°C above the alpha transus temperature T ⁇ .
  • the gamma titanium aluminide alloy is maintained at the temperature T 1 for up to 2 hours.
  • the gamma titanium aluminide alloy is then quenched, for example fluidised bed cooled, or salt bath cooled, to a temperature T 2 about 900°C to 1200°C and maintained for a predetermined time period to induce a massively transformed gamma microstructure.
  • the gamma titanium alloy is heated to a temperature T 3 about 30°C to 60°C below the alpha transus temperature T ⁇ .
  • the gamma titanium aluminide alloy is maintained at the temperature T 3 for up to 4 hours to precipitate fine alpha plates with different orientations in the massively transformed gamma microstructure due to the massive gamma to alpha + gamma phase transformation. This gives rise to a very fine duplex microstructure.
  • the differently orientated alpha plates precipitated in the massive gamma phase matrix effectively reduce the grain size of the gamma titanium aluminide.
  • the gamma titanium aluminide alloy is then cooled, for example air cooled, or furnace cooled, to ambient temperature.
  • the holding at temperature T 1 for a time period t 1 also acts a homogenisation process for cast titanium aluminide alloys.
  • a gamma titanium aluminide alloy consisting of 46at% aluminium, 8at% niobium, up to 0.07at% carbon and the balance titanium plus incidental impurities was heat treated according to the present invention.
  • the gamma titanium aluminide alloy was fluidised bed, or salt bath, quenched to a temperature 900°C ⁇ T 2 ⁇ 1200°C and was held at temperature T 2 , where 900°C ⁇ T 2 ⁇ 1200°C, for a sufficient time to allow the massive transformation to go to completion.
  • the gamma titanium aluminide alloy was air cooled to ambient temperature.
  • the gamma titanium aluminide alloy is air-cooled or oil cooled from temperature T 2 to ambient temperature before the gamma titanium aluminide alloy is heated to the temperature T 3 .
  • the present invention is applicable to a gamma titanium aluminide alloy consisting of 46at% aluminium, 5at% niobium, 0.3at% boron, 0.2at% carbon and the balance titanium plus incidental impurities.
  • the present invention is applicable to a gamma titanium aluminide alloy consisting of 47at% aluminium, 2at% niobium, 1at% tungsten, 1at% chromium, 1at% boron, 0.2at% silicon and the balance titanium plus incidental impurities.
  • the present invention is applicable to gamma titanium aluminide alloy consisting of 47at% aluminium, 2at% tantalum, 1at% chromium, 1at% manganese, 1at% boron, 0.2at% silicon and the balance titanium plus incidental impurities.
  • the present invention is also applicable to gamma titanium aluminide alloy consisting of 46at% aluminium, 5at% niobium, 1at% tungsten and the balance titanium plus incidental impurities.
  • the present invention is applicable to a gamma titanium aluminide alloy consisting of 45-46at% aluminium, 8at% niobium, up to 0.07at% carbon and the balance is titanium and incidental impurities.
  • the present invention is also applicable to a gamma titanium aluminide alloy consisting of 45-46at% aluminium, 2-6at% niobium, 2-6at% hafnium and the balance is titanium plus incidental impurities.
  • the present invention is also applicable to a gamma titanium aluminide alloy consisting of 48at% aluminium, 2at% chromium, 2at% niobium and the balance titanium and incidental impurities.
  • the advantages of the present invention are that the cooling, quenching, of the titanium aluminide from above the alpha transus to an intermediate temperature induces reduced levels of quenching stresses compared to cooling, quenching, to ambient temperature as described in our European patent application no. 03253539.5.
  • a further advantage is that at temperatures above about 1000°C the titanium aluminide is relatively ductile and the quenching stresses do not cause fracture.
  • the heat-treatment is suitable for relatively thin castings and for larger castings so that they all have improved ductility and high strength. Also the heat-treatment is applicable to compositions of titanium aluminide with a broader range, a lower level, of aluminium and hence it is applicable to stronger titanium aluminide alloys.
  • the lower level of aluminium may be 45at% and possibly 44at%.
  • the present invention provides a heat treatment for gamma titanium aluminide alloy components, which provides grain refinement. It is particularly suitable for relatively large and complex shaped cast components where the previous heat treatment would induce high residual stresses and possibly cracking of the gamma titanium aluminide alloy components.
  • the heat treatment also permits grain refinement throughout relatively large and complex shaped components rather than just the surface regions of the component.
  • titanium aluminide alloy component may be heated to a temperature of about 1300°C and to maintain the titanium aluminide alloy component at about 1300°C to allow the temperature to equilibrate in the titanium aluminide alloy component so that the titanium aluminide alloy component needs to be maintained at temperature T 1 for a shorter time period.
  • the cast gamma titanium aluminide alloy component may be hot isostatically pressed (HIP) to remove the porosity.
  • the hot isostatic pressing preferably occurs at the same time as the heat treatment temperature T 2 and for the time period of about 4 hours at a pressure of about 150MPa and this is beneficial because this dispenses with the requirement for a separate hot isostatic pressing step.
  • the present invention is particularly suitable for gamma titanium aluminide gas turbine engine compressor blades as illustrated in figure 2.
  • the compressor blade 10 comprises a root 12, a shank 14, a platform 16 and an aerofoil 18.
  • the present invention is also suitable for gamma titanium aluminide gas turbine engine compressor vanes or other gamma titanium aluminide gas turbine engine components.
  • the present invention may also be suitable for gamma titanium aluminide components for other engine, machines or applications.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04254344A 2003-08-14 2004-07-21 Procédé pour le traitement thermique des alliages de TiAl Withdrawn EP1507017A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0319061 2003-08-14
GBGB0319061.8A GB0319061D0 (en) 2003-08-14 2003-08-14 A method of heat treating titanium aluminide

Publications (1)

Publication Number Publication Date
EP1507017A1 true EP1507017A1 (fr) 2005-02-16

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EP04254344A Withdrawn EP1507017A1 (fr) 2003-08-14 2004-07-21 Procédé pour le traitement thermique des alliages de TiAl

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US (1) US20050081967A1 (fr)
EP (1) EP1507017A1 (fr)
GB (1) GB0319061D0 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1813691A1 (fr) * 2006-01-27 2007-08-01 Rolls-Royce plc Procédé pour le traitement thermique d'aluminure de titane
EP1889939A3 (fr) * 2006-08-19 2008-10-29 Rolls-Royce plc Alliage et procédé pour le traitement d'aluminure de titane
CN105039886A (zh) * 2015-08-05 2015-11-11 西部超导材料科技股份有限公司 一种具有均匀细小组织相Zr-2.5Nb合金棒材的制备方法
EP3360983A1 (fr) * 2017-02-14 2018-08-15 General Electric Company Alliages d'aluminium de titane et composants de turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2503738C2 (ru) * 2012-03-02 2014-01-10 Федеральное государственное бюджетное учреждение науки Институт проблем сверхпластичности металлов Российской академии наук (ИПСМ РАН) СПОСОБ ТЕРМИЧЕСКОЙ ОБРАБОТКИ ЛИТЫХ ЗАГОТОВОК ИЗ ЗАЭВТЕКТОИДНЫХ ИНТЕРМЕТАЛЛИДНЫХ СПЛАВОВ НА ОСНОВЕ ФАЗ γ-TiAl+α2-Ti3Al

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5205875A (en) * 1991-12-02 1993-04-27 General Electric Company Wrought gamma titanium aluminide alloys modified by chromium, boron, and nionium
JPH06116691A (ja) * 1992-10-05 1994-04-26 Mitsubishi Materials Corp ＴｉＡｌ金属間化合物系Ｔｉ合金の熱処理法
EP1308529A1 (fr) * 2001-11-05 2003-05-07 Mitsubishi Heavy Industries, Ltd. Composé intermetallique d'alliage à base de titane-aluminium et la méthode pour fabriquer un produit en cet alliage
EP1378582A1 (fr) * 2002-07-05 2004-01-07 ROLLS-ROYCE plc Procédé pour le traitement thermique des alliages de TiAl

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4208485C2 (de) * 1992-03-17 1997-09-04 Wuenning Joachim Verfahren und Vorrichtung zum Abschrecken metallischer Werkstücke
US6231699B1 (en) * 1994-06-20 2001-05-15 General Electric Company Heat treatment of gamma titanium aluminide alloys
US5634992A (en) * 1994-06-20 1997-06-03 General Electric Company Method for heat treating gamma titanium aluminide alloys
US5558729A (en) * 1995-01-27 1996-09-24 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
USH1659H (en) * 1995-05-08 1997-07-01 The United States Of America As Represented By The Secretary Of The Air Force Method for heat treating titanium aluminide alloys
US5653828A (en) * 1995-10-26 1997-08-05 National Research Council Of Canada Method to procuce fine-grained lamellar microstructures in gamma titanium aluminides

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5205875A (en) * 1991-12-02 1993-04-27 General Electric Company Wrought gamma titanium aluminide alloys modified by chromium, boron, and nionium
JPH06116691A (ja) * 1992-10-05 1994-04-26 Mitsubishi Materials Corp ＴｉＡｌ金属間化合物系Ｔｉ合金の熱処理法
EP1308529A1 (fr) * 2001-11-05 2003-05-07 Mitsubishi Heavy Industries, Ltd. Composé intermetallique d'alliage à base de titane-aluminium et la méthode pour fabriquer un produit en cet alliage
EP1378582A1 (fr) * 2002-07-05 2004-01-07 ROLLS-ROYCE plc Procédé pour le traitement thermique des alliages de TiAl

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1813691A1 (fr) * 2006-01-27 2007-08-01 Rolls-Royce plc Procédé pour le traitement thermique d'aluminure de titane
US7704339B2 (en) 2006-01-27 2010-04-27 Rolls-Royce Plc Method of heat treating titanium aluminide
EP1889939A3 (fr) * 2006-08-19 2008-10-29 Rolls-Royce plc Alliage et procédé pour le traitement d'aluminure de titane
CN105039886A (zh) * 2015-08-05 2015-11-11 西部超导材料科技股份有限公司 一种具有均匀细小组织相Zr-2.5Nb合金棒材的制备方法
CN105039886B (zh) * 2015-08-05 2017-02-01 西部超导材料科技股份有限公司 一种具有均匀细小组织相Zr‑2.5Nb合金棒材的制备方法
EP3360983A1 (fr) * 2017-02-14 2018-08-15 General Electric Company Alliages d'aluminium de titane et composants de turbine

Also Published As

Publication number Publication date
GB0319061D0 (en) 2003-09-17
US20050081967A1 (en) 2005-04-21

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