EP2851445B1 - Alliage TiAl résistant au fluage - Google Patents
Alliage TiAl résistant au fluage Download PDFInfo
- Publication number
- EP2851445B1 EP2851445B1 EP13185280.8A EP13185280A EP2851445B1 EP 2851445 B1 EP2851445 B1 EP 2851445B1 EP 13185280 A EP13185280 A EP 13185280A EP 2851445 B1 EP2851445 B1 EP 2851445B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- tial
- annealing
- temperature
- heat treatment
- 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.)
- Not-in-force
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- 229910045601 alloy Inorganic materials 0.000 title claims description 40
- 239000000956 alloy Substances 0.000 title claims description 40
- 229910010038 TiAl Inorganic materials 0.000 title claims description 30
- 238000000137 annealing Methods 0.000 claims description 19
- 238000010438 heat treatment Methods 0.000 claims description 17
- 229910052799 carbon Inorganic materials 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 15
- 229910052782 aluminium Inorganic materials 0.000 claims description 13
- 229910052758 niobium Inorganic materials 0.000 claims description 12
- 229910021325 alpha 2-Ti3Al Inorganic materials 0.000 claims description 11
- 229910052796 boron Inorganic materials 0.000 claims description 11
- 229910052750 molybdenum Inorganic materials 0.000 claims description 11
- 229910052710 silicon Inorganic materials 0.000 claims description 11
- 230000032683 aging Effects 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 5
- 239000000126 substance Substances 0.000 claims description 4
- 229910006281 γ-TiAl Inorganic materials 0.000 claims description 4
- 239000013067 intermediate product Substances 0.000 claims 1
- 239000010936 titanium Substances 0.000 description 16
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 10
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 10
- 229910052719 titanium Inorganic materials 0.000 description 10
- 239000010955 niobium Substances 0.000 description 9
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 9
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 8
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 8
- 239000011733 molybdenum Substances 0.000 description 8
- 239000010703 silicon Substances 0.000 description 8
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 7
- 230000001413 cellular effect Effects 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 6
- 229910021332 silicide Inorganic materials 0.000 description 4
- 238000005242 forging Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 3
- 150000001247 metal acetylides Chemical class 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000001953 recrystallisation Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 229910052738 indium Inorganic materials 0.000 description 2
- 229910052748 manganese Inorganic materials 0.000 description 2
- 239000011572 manganese Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002244 precipitate Substances 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- -1 20 to 25 vol.% Inorganic materials 0.000 description 1
- 206010037660 Pyrexia Diseases 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000012946 outsourcing Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000011282 treatment Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- 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
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
-
- 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
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
Definitions
- the present invention relates to a method for the production of a component from a TiAl alloy, which besides niobium and aluminum comprises niobium and molybdenum and / or manganese and is referred to in the art as TNM alloy.
- TiAl alloys based on the ⁇ -TiAl intermetallic phase are predestined for applications in turbomachines, such as stationary gas turbines and aircraft engines, due to their low specific weight and the high strength due to the ordered intermetallic phase.
- turbomachines such as stationary gas turbines and aircraft engines
- the US 2011/0189026 A1 a TiAl - based alloy for the manufacture of gas turbine components.
- the alloy described therein is a so-called TNM alloy which, in addition to 42 to 45 at.% Aluminum, contains 3 to 8 at.% Niobium and 0.2 to 3 at.% Molybdenum and / or manganese.
- 0.1 to 1 at.% Boron and / or carbon and / or silicon may be included.
- the remainder of the alloy is formed by titanium.
- Such alloys which in particular have 43.5 at.% Aluminum, 4 at.% Niobium, 1 at.% Molybdenum and 0.1 percent boron with the remainder of titanium, are suitable for use at operating temperatures of 750 ° C. to 780 ° C suitable.
- TNM alloys is complexly composed of several phases and comprises ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o / B2 - titanium.
- Another alloy with a structure of ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ - phase is in US 2011/0277891 A1 described.
- This alloy has 42 to 44.5 at.% Aluminum, 3.5 to 4.5 at.% Niobium, 0.5 to 1.5 percent molybdenum, up to 2.2 at.% Manganese, 0.05 to 0 , 2 at.% Boron, 0.001 to 0.01 at.% Silicon, 0.001 to 1.0 at.% Carbon, 0.001 to 0.1 at.% Oxygen, 0.0001 to about 0.002 at.% Nitrogen and the balance titanium and impurities on.
- TiAl alloys are from the documents WO 2012/041276 A2 and EP 2 620 517 A1 known.
- TNM alloys are limited to temperatures below 800 ° C, as with prolonged use at higher temperatures an insufficient Creep resistance is observed, which has an insufficient life for use in turbomachinery, such as stationary gas turbine or aircraft engines result.
- the present invention makes it possible to improve the known TNM alloys in their creep resistance and thus to increase the possible use temperatures.
- the known composition of the TNM alloys it is proposed to limit the aluminum content to a maximum of 43 at.%.
- the combined and targeted reduction of the aluminum content and the simultaneous provision of certain proportions of carbon and silicon can significantly improve the creep resistance of a corresponding TiAl alloy and thus increase the operating temperature in the range of 800 to 850 ° C.
- the chemical composition of a corresponding alloy can not exceed 43 at.% Aluminum, 3 to 8 at.% Niobium, 0.2 at.% To 3 at.% Molybdenum and / or manganese, 0.05 at.% To 0.5 % boron, 0.1 at.% to 0.5 at.% carbon, 0.1 at.% to 0.5 at.% silicon, and the balance titanium and unavoidable impurities.
- the TiAl alloy may be at most 43 at.% Aluminum, 3.5 at.% To 4.5 at.% Niobium, 0.8 at.% To 1.2 at.% Molybdenum and / or manganese, 0.05 % to 0.15 at.% boron, 0.2 at.% to 0.4 at.% carbon, 0.2 at.% to 0.4 at.% silicon and the balance titanium and unavoidable impurities.
- a TiAl alloy has proved to be advantageous which contains 43 at.% Aluminum, 4 at.% Niobium, 1 at.% Molybdenum, 0.1 at.% Boron, 0.3 at.% Carbon, 0.3 at. % Silicon and the rest titanium and unavoidable impurities.
- the specified values are not absolute values, but represent target values, from which within the limits of the technical feasibility can be deviated, which are thus adjustable according to the accepted rules of technology in a certain accuracy range.
- Such an alloy has a microstructure at room or operating temperatures which has the phases ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o / B2 - titanium, the B2 or ⁇ o phase being an ordered variant of the ⁇ - Titans represents.
- a corresponding component with a TiAl alloy can be produced by casting with or without subsequent cold and / or hot working according to the invention.
- a common method for producing corresponding components of turbomachines, such as turbine blades, is to cast a blank and then hot-form it by forging.
- a suitably prepared intermediate may be subjected to a heat treatment according to the present invention comprising annealing at a temperature between 800 ° C and 900 ° C for 4 to 8 hours. Such stabilization annealing can be used to optimize the desired microstructure of a TNM alloy for improved creep resistance.
- the annealing may take place at a temperature of or around 850 ° C for 6 hours.
- the corresponding component can be cooled rapidly, for example to ambient atmosphere or by flowing with a cooling gas.
- the heat treatment may include, in addition to the above-described annealing, additional heat treatment steps that take place before annealing.
- the heat treatment can be configured in two stages with an aging upstream of the annealing.
- the use of the terms outsourcing and annealing here does not indicate fundamentally different process mechanisms, but merely serves to distinguish the heat treatment stages.
- thermomechanical treatments it is possible to carry out further thermal and / or thermomechanical treatments before or after the heat treatment described here.
- the heat treatment described herein should be the final heat treatment.
- the aging as the first stage of a two-stage heat treatment may take place at a temperature of 950 ° C to 1300 ° C for 0.1 hour to 2 hours.
- the aging can take place at a temperature of 950 ° C to 1050 ° C or 1200 ° C to 1300 ° C for a period of 0.25 hours to 1 hour.
- a TiAl alloy with the presented composition and a component made of a corresponding TiAl alloy, which has been subjected in particular to the presented production method with the heat treatment according to the invention, can advantageously be used for components of turbomachines, such as, for example, blades of a turbomachine.
- the components can be used at temperatures up to 850 ° C, in particular in the operating temperature range from 800 ° C to 830 ° C, wherein operating temperature here means that the corresponding temperature occurs permanently during operation or the temperature can occur as a peak temperature in the short term during operation ,
- the attached figure shows in a microsection a typical structure of a material according to the invention.
- a blade of an aircraft engine can be made by first casting and hot isostatically pressing the above TNM alloy. Thereafter, it is subjected to fine - grain forging by Hot Die forging above the dissolution temperature of the ⁇ - TiAl phase (T ⁇ solv ⁇ 1260 ° C), whereby dynamic recrystallization of the disordered ⁇ - titanium phase results in a nearly texture - free and fine - grained microstructure with a mean grain size ⁇ - phase of ⁇ 10 microns can be adjusted.
- the fine - grained and supersaturated TNM alloy is subjected to a two - stage heat treatment.
- a targeted ⁇ -lamella width is set for the first removal in order to optimize the creep properties ("short-time annealing").
- phase fractions are set close to the thermodynamic equilibrium (“long-term annealing”).
- the heat treatment process for the microstructure with a particularly good creep resistance takes place, for example, with an aging at 1000 ° C. for 15 minutes with a subsequent rapid cooling and annealing at 850 ° C. for 6 hours and likewise rapid cooling.
- the first removal leads to the formation of a cellular reaction phase (ZR) starting from the limits of the ⁇ 2 -Ti 3 Al / ⁇ -TiAl colonies, which occurs in different amounts depending on the aging temperature and duration and represents a transformation structure.
- ZR cellular reaction phase
- the driving force for the cellular reaction and the corresponding formation of the cellular reaction phase comes to a standstill because of the larger lamellar spacing.
- the described method results in combination with the selected material with less effort compared to the previous methods to significantly improved mechanical properties. Avoiding high-temperature annealing prevents the risk of grain growth.
- a correspondingly produced component such as, for example, a blade of an aircraft engine, has improved creep resistance compared to previously known TiAl alloys and in particular TNM alloys.
- a characteristic structure of a component of a TiAl alloy produced according to the invention is shown in the attached figure.
- This microstructure is a nearly lamellar microstructure with small amounts of ⁇ o - phase in the order of ⁇ 5 vol.% (NL ⁇ ).
- the ⁇ o - titanium phase can be linear or globular. Within the ⁇ o phase are lenticular ⁇ - TiAl precipitates.
- the structure consists with up to 98 vol.% Mainly of globular ⁇ 2 - Ti 3 Al / ⁇ - TiAl colonies with a maximum size of ⁇ 10 - 20 ⁇ m and an average width of the ⁇ - TiAl lamellae of the order of 50 - 150 nm. In general, there are no globular y grains, which can lead to a reduction of the creep resistance from a volume fraction of about> 5%.
- the volume fraction of cellular reaction phase (ZR) is less than 10 vol.%.
- the microstructure of a corresponding component may comprise from about 70 to 80 vol.%, In particular about 75 vol.% ⁇ - TiAl, 20 to 25 vol.%, In particular about 23 vol.% ⁇ 2 - Ti 3 Al and 1 to 3 vol.%, in particular about 2 vol.% ⁇ o - Ti.
- the carbon is mainly present in solution.
- cellular reaction phase (ZR) may additionally be present in the structure, wherein the structural constituents are of course to 100 vol.% and wherein the cellular reaction phase is assigned to the proportions of ⁇ - TiAl and ⁇ 2 - Ti 3 Al.
- the microstructural fractions of ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o - Ti hardly change, ie the microstructure remains stable, but the creep under conditions of use leads to the precipitation of very fine carbides within the ⁇ -TiAl phase, eg in the form of P-Ti 3 AlC, which contribute to the hindrance of dislocation creep and thus to an increase in creep resistance.
- the finest silicide precipitates ( ⁇ - Ti 5 Si 3 ) at the ⁇ 2 - Ti 3 Al / ⁇ - TiAl interfaces improve the microstructure stability. Residues of coarser silicides can be contained in the microstructure depending on the choice of the forming and heat treatment parameters.
- the fine - grained NL ⁇ microstructure is characterized by high high - temperature strength, creep resistance and microstructure stability with significantly improved damage tolerance below the brittle - ductile transition temperature due to the small size and globular form of the ⁇ 2 - Ti 3 Al / ⁇ - TiAl colonies.
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- 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)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (10)
- Procédé de préparation d'un composant en alliage TiAl pour applications à haute température, constitué de la composition chimique suivante :au plus 43 % en pourcentage atomique d'Al,3 à 8 % en pourcentage atomique de Nb,0,2 à 3 % en pourcentage atomique de Mo et/ou de Mn,0,05 à 0,5 % en pourcentage atomique de B,0,1 à 0,5 % en pourcentage atomique de C,0,1 à 0,5 % en pourcentage atomique de Si,le reste étant du Ti et des impuretés inévitables, caractérisé en ce qu'un produit intermédiaire coulé et/ou transformé à froid et/ou à chaud est fourni à partir de l'alliage, lequel produit est soumis à un traitement thermique comprenant un recuit à une température comprise entre 800 et 900 °C pendant 4 à 8 heures.
- Procédé selon la revendication 1, caractérisé en ce que le recuit a lieu à une température d'environ 850 °C pendant 6 heures.
- Procédé selon la revendication 1 ou 2, caractérisé en ce que le recuit est fini par un refroidissement rapide.
- Procédé selon l'une des revendications 1 à 3, caractérisé en ce que le traitement thermique s'effectue en deux étapes et le recuit est la seconde étape du traitement thermique.
- Procédé selon l'une des revendications 1 à 4, caractérisé en ce que le recuit est précédé d'une exposition qui constitue la première étape du traitement thermique.
- Procédé selon la revendication 5, caractérisé en ce que l'exposition a lieu à une température comprise entre 950 °C et 1300 °C pendant 0,1 à 2 h.
- Procédé selon la revendication 5 ou 6, caractérisé en ce que l'exposition a lieu à une température comprise entre 950 °C et 1 050 °C ou 1 200°C et 1 300 °C pendant 0,25 à 1 heure.
- Procédé selon l'une des revendications 1 à 7, caractérisé en ce que l'alliage présente la composition chimique suivante :au plus 43 % en pourcentage atomique d'Al,3,5 à 4,5 % en pourcentage atomique de Nb,0,8 à 1,2 % en pourcentage atomique de Mo et/ou de Mn, 0,05 à 0,15 % en pourcentage atomique de B,0,2 à 0,4 % en pourcentage atomique de C,0,2 à 0,4 % en pourcentage atomique de Si,et le reste est du Ti.
- Procédé selon l'une des revendications 1 à 8, caractérisé en ce que l'alliage présente la composition chimique suivante :43 % en pourcentage atomique d'Al,4 % en pourcentage atomique de Nb,1 % en pourcentage atomique de Mo,0,1 % en pourcentage atomique de B,0,3 % en pourcentage atomique de C,0,3 % en pourcentage atomique de Siet le reste est du Ti.
- Procédé selon l'une des revendications 1 à 9, caractérisé en ce que l'alliage se présente à température ambiante comme suit : γ - TiAl,α2 - Ti3Al et β0/B2 - Ti.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES13185280T ES2747155T3 (es) | 2013-09-20 | 2013-09-20 | Aleación de TiAl resistente a la fluencia |
EP13185280.8A EP2851445B1 (fr) | 2013-09-20 | 2013-09-20 | Alliage TiAl résistant au fluage |
US14/481,295 US9994934B2 (en) | 2013-09-20 | 2014-09-09 | Creep-resistant TiA1 alloy |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13185280.8A EP2851445B1 (fr) | 2013-09-20 | 2013-09-20 | Alliage TiAl résistant au fluage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2851445A1 EP2851445A1 (fr) | 2015-03-25 |
EP2851445B1 true EP2851445B1 (fr) | 2019-09-04 |
Family
ID=49226043
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13185280.8A Not-in-force EP2851445B1 (fr) | 2013-09-20 | 2013-09-20 | Alliage TiAl résistant au fluage |
Country Status (3)
Country | Link |
---|---|
US (1) | US9994934B2 (fr) |
EP (1) | EP2851445B1 (fr) |
ES (1) | ES2747155T3 (fr) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3012410B1 (fr) * | 2014-09-29 | 2023-05-10 | Raytheon Technologies Corporation | Composants de tial gamma avancé |
CN104878452A (zh) * | 2015-05-13 | 2015-09-02 | 南京理工大学 | 一种高温高强TiAl-Nb单晶及其制备方法 |
US20180010213A1 (en) * | 2016-07-07 | 2018-01-11 | United Technologies Corporation | Enhance ductility of gamma titanium aluminum alloys by reducing interstitial contents |
US20180010468A1 (en) * | 2016-07-07 | 2018-01-11 | United Technologies Corporation | Enhanced temperature capability gamma titanium aluminum alloys |
ES2891724T3 (es) | 2016-07-12 | 2022-01-31 | MTU Aero Engines AG | Aleación de TiAl resistente a altas temperaturas, método para fabricar un componente de una aleación de TiAl correspondiente y componente de una aleación de TiAl correspondiente |
CN110512116B (zh) * | 2019-09-09 | 2021-03-26 | 中国航发北京航空材料研究院 | 一种多组元高合金化高Nb-TiAl金属间化合物 |
CN112620488A (zh) * | 2020-12-16 | 2021-04-09 | 西部超导材料科技股份有限公司 | 一种Ti3Al层状复合板及其制备方法 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5350466A (en) * | 1993-07-19 | 1994-09-27 | Howmet Corporation | Creep resistant titanium aluminide alloy |
DE102007051499A1 (de) | 2007-10-27 | 2009-04-30 | Mtu Aero Engines Gmbh | Werkstoff für ein Gasturbinenbauteil, Verfahren zur Herstellung eines Gasturbinenbauteils sowie Gasturbinenbauteil |
DE102009050603B3 (de) * | 2009-10-24 | 2011-04-14 | Gfe Metalle Und Materialien Gmbh | Verfahren zur Herstellung einer β-γ-TiAl-Basislegierung |
AT509768B1 (de) | 2010-05-12 | 2012-04-15 | Boehler Schmiedetechnik Gmbh & Co Kg | Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung |
US8876992B2 (en) * | 2010-08-30 | 2014-11-04 | United Technologies Corporation | Process and system for fabricating gamma TiAl turbine engine components |
WO2012041276A2 (fr) * | 2010-09-22 | 2012-04-05 | Mtu Aero Engines Gmbh | Alliage tial résistant à la chaleur |
DE102011110740B4 (de) * | 2011-08-11 | 2017-01-19 | MTU Aero Engines AG | Verfahren zur Herstellung geschmiedeter TiAl-Bauteile |
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 |
EP2620517A1 (fr) * | 2012-01-25 | 2013-07-31 | MTU Aero Engines GmbH | Alliage TiAl thermostable |
-
2013
- 2013-09-20 EP EP13185280.8A patent/EP2851445B1/fr not_active Not-in-force
- 2013-09-20 ES ES13185280T patent/ES2747155T3/es active Active
-
2014
- 2014-09-09 US US14/481,295 patent/US9994934B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
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Also Published As
Publication number | Publication date |
---|---|
US20150086414A1 (en) | 2015-03-26 |
ES2747155T3 (es) | 2020-03-10 |
US9994934B2 (en) | 2018-06-12 |
EP2851445A1 (fr) | 2015-03-25 |
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