CN101056998A - Titanium Aluminum Alloy - Google Patents
Titanium Aluminum Alloy Download PDFInfo
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- CN101056998A CN101056998A CNA2005800390124A CN200580039012A CN101056998A CN 101056998 A CN101056998 A CN 101056998A CN A2005800390124 A CNA2005800390124 A CN A2005800390124A CN 200580039012 A CN200580039012 A CN 200580039012A CN 101056998 A CN101056998 A CN 101056998A
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
- B22D21/002—Castings of light metals
- B22D21/005—Castings of light metals with high melting point, e.g. Be 1280 degrees C, Ti 1725 degrees C
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Abstract
The invention relates to a titanium-aluminium-based alloy produced by applying melt-metallurgical and powder-metallurgical techniques, said alloy having an alloy composition of Ti-zAl-yNb, wherein z is between 44.5 and 45.5 atom%, y is between 5 and 10 atom%, and possible additions B and/or C, the content of B and/or C being between 0.05 and 0.8 atom%. The alloy is characterized in that the alloy contains 0.1 atomic% to 3.0 atomic% of molybdenum .
Description
Technical field
The present invention relates to a kind of by using the titanium aluminium base alloy that fusion smelting technology and powder metallurgy technology are made, its alloy composition that has is Ti-zAl-yNb, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom %, and possible additive B and/or C, its content is between 0.05 atom % and 0.8 atom %.
Background technology
Titanium aluminum alloy has following characteristic, is about to titanium aluminum alloy as lightweight structural material, and particularly the lightweight structural material of at high temperature using is particularly advantageous.Very interested for this special alloy on industrial application, this alloy is based on intermetallic phase γ with tetragonal-(TiAl), and also contains the intermetallic phase α that has hexagonal structure on a small quantity except main phase γ-(TiAl)
2(Ti
3Al).This γ-titanium aluminium-alloy is because the little (3.85～4.2g/cm of density
3), Young's modulus height, intensity are high and loom large until the characteristic of 700 ℃ creep strength, these characteristics make this alloy attractive as the material of mobile member under the use temperature that has raise.Example to this is the turbine blade in aircraft drive unit and the land-based gas turbine engine, the valve and the hot gas ventilation installation of engine.
At aluminium content is in the key areas of the alloy technology between 45 atom % and the 49 atom %, when the curing (solidifying) of melts and cooling subsequently a series of phase change can take place.Solidify or finish by β-mixed crystal fully or (peritectic peritektischen) is finished in the reaction, the α-mixed crystal with hexagonal structure and γ-participate in wherein mutually at two peritectoids with body-centred cubic structure (high temperature phase).
Be known that in addition elemental niobium (Nb) causes intensity, creep strength and oxidation-resistance, and the raising of ductibility.Utilization is insoluble basically element boron in γ-mutually, the state but also utilize the thermal treatment in α-zone subsequently can reach meticulous crystallization (Kornfeinung) after deformation of not only casting.The raised portion of β-phase in structure because the concentration of low-aluminum-content and high beta stable element can cause this more serious dispersion mutually, and plays the effect that makes the mechanical characteristics variation.
The mechanical characteristics of γ-titanium aluminium-alloy is anisotropic strongly, and this is based on the behavioral trait of its deformation characteristic and fracture, also because the preferred sheet structure of regulating or the structural anisotropy of dual-structure.For autotelic adjustment structure and structure, when making member, adopt casting process, different powder metallurgy process and the combination of deformation method and these manufacture method by titanium aluminium.
By Y-W.Kim and D.M.Dimiduk at publication " Structural Intermetallics (structural metal is changed thing mutually) 1997 ", Eds.M.V.Nathal, R.Darolia, C.T.Liu, P.L.Martin, D.B.Miracle, R.Wagner, M.Yamaguchi, TMS, Warrendale PA, 1996, (document) known in the 531st page, in different research projects, studied a large amount of alloying elements at structure, different preparation method and the action characteristic aspect the structure adjusting under the characteristic situation separately.It is similar and complicated that the pass of being found ties up to this, as its structural metal at other, as the situation of steel, and should relation can only summarize with the form of restriction and very common form in principle.Therefore, the combination that can have characteristic aspect brilliance through definite composition.
The common problem of all titanium aluminum alloies is that its ductility is less.Up to now, it is (the reference " Structural Intermetallics (structural metal is changed thing mutually) 1997 " that can't realize that the high fragility of the titanium aluminum alloy that provides in advance by the essence of intermetallic phase and little damage deviation improve fatefully by the effect of alloy, the 531st page, on seeing).Though for the application described in the preface can reach 〉=1% repeatedly plasticity extends.Yet, make turbine and engine and require the bottom line of this ductility in industrial production, to guarantee by bigger initial value.Because ductility is responsive relevant with structure,, promptly guarantee to constitute by uniform structure as far as possible so this is very difficult in Industrial processes.Particle aggregation district size or lamella accumulation area size for permissible maximum damage intensity of high-intensity alloy such as maximum are especially little, make to have very high structural uniformity for such alloy expectation.Yet this structural uniformity because alloy composition inevitably changes, as the Al-content of ± 0.5 atom %, can only be realized very difficultly.
Now, in the possible structure type of many γ-titanium aluminum alloies, it is admissible having only laminated structure or so-called dual structure to use for high temperature.When cooling the single-phase zone from α-mixed crystal at first generate, in this zone the layer of γ-phase with crystallography (mode) directionally from α-mixed crystal segregation (precipitation) come out.
In contrast, when annealing in the two phase region of material at α+γ, formed the dual structure that constitutes by lamella accumulation area and γ-particle.At this, existing α-particle is transformed into biphase lamella accumulation area again when cooling.The integral part of coarse texture at first generates in γ-titanium aluminum alloy like this, promptly forms big α-particle when passing α-zone.This can occur when solidifying, and promptly forms big α-phase styloid by melts.Therefore, must add the single-phase zone of avoiding α-mixed crystal man-hour as far as possible.Yet, because change (fluctuation) appears in actual moiety and process temperature, and the appearance of the local structure in workpiece change, therefore, inevitably formed thick lamella accumulation area.
Summary of the invention
Based on this prior art, the objective of the invention is to, providing a kind of has thin and titanium aluminum alloy structural form uniformly, wherein, the variation of the alloy composition that in industrial practice, occurs and in manufacturing processed inevitably temperature variation the homogeneity of alloy is not almost acted on when particularly manufacture method has radical change or acts on worth mentioning.In addition, the present invention also aims to, a kind of member of homogeneous alloy is provided.
Purpose of the present invention realizes by means of using fusion metallurgy technology and the prepared titanium aluminium base alloy of powder metallurgy technology, this alloy has the alloy composition of Ti-zAl-yNb, 44.5 atom %≤z≤47 atom % wherein, be preferably 44.5 atom %≤z≤45.5 atom %, and 5 atom %≤y≤10 atom %, this alloy further comprises the molybdenum (Mo) of 0.1 atom % to 3.0 atom %, and the remainder of alloy is made of Ti (titanium).
Demonstrate in test, by in titanium aluminum alloy, adding molybdenum element with niobium composition, at this, usually be no more than the β of whole temperature range-be stable mutually, therefore, the remainder of high temperature-β-phase decomposes when traditional processing step (as extruding), reaches better alloy structure homogeneity.Thereby surpass whole, during with preparation process relevant temperature scope, realizes the volume composition of the β-phase of no particle increase.This according to alloy species of the present invention because meticulous and very homodisperse β-phase has the uniform texture of intensity values.
Therefore, provide a kind of alloy, this alloy is suitable for the light member material of application under the high temperature, as the member of turbine blade or engine component and turbine.
Alloy according to the present invention is to make under the situation of application casting metallurgy, fusion metallurgy or powder metallurgic method or these methods and improvement technical tie-up application.
At first, to be added into content be 1.0 atom % forms the good microtexture with high structural uniformity to the molybdenum of 3.0 atom % to Ti-(44.5 atom % are to 45.5 atom %) Al-(5 atom % are to 10 atom %) Nb.
In addition, alloy according to the present invention has the composition of Ti-zAl-yNb-xB, 44.5 atom %≤z≤47 atom % wherein, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom % and 0.05 atom %≤x≤0.8 atom %, the composition that perhaps has Ti-zAl-yNb-wC, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom % and 0.05 atom %≤w≤0.8 atom %, every kind of composition contains the molybdenum (Mo) of 0.1 atom % to 3 atom %.
Alternatively, constitute alloy by Ti-zAl-yNb-xB-wC, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom %, 0.05 atom %≤x≤0.8 atom % and 0.05 atom %≤w≤0.8 atom %, and contain the molybdenum (Mo) of 0.1 atom % extraly to 3 atom %.
By given alloy and corresponding alloy content, generate high-intensity γ-titanium aluminum alloy with fine dispersion β-phase for technological temperature a wider range.
In the present invention, structural stability of being made every effort to and process safety reach like this, promptly by on purpose add body-centred cubic β-phase avoid occurring surpassing whole, in the single-phase zone of manufacturing processed and the temperature range followed in use.In principle under the titanium aluminum alloy situation of all technology, β-occur mutually as the high temperature of temperature 〉=1350 ℃.
Know by documents and materials, thisly can pass through many different elements mutually, more be stabilized under the low temperature as Mo, W, Nb, Cr, Mn and V.Yet the special problem when adding these alloying elements is, must very accurately determine the content of the beta stable element relevant with Al content.In addition, when being added into these elements, undesirable interaction occurred, this interaction causes β-phase part higher and cause the rough segmentation of this phase to be loose.This structure is very unfavorable for mechanical property.
In addition, the characteristic of β-phase is also relevant with every kind of alloying element and composition thereof.Especially, choice structure promptly will be avoided as much as possible from β-brittle ω-phase is separated out like this.Provide alloy composition according to this relation, adopted this alloy composition can realize and be used for dispersive β-phase under the technological temperature of relative broad range for the optimized composition of mechanical property.Obtain good as far as possible strength property simultaneously.
According to an embodiment preferred of the present invention, alloy also contains boron, and preferably, the boron content in the alloy is that 0.05 atom % is to 0.8 atom %.The interpolation of boron has advantageously generated stable crystallization (Ausscheidungen), and this crystallization helps according to the mechanical hardening of alloy of the present invention and the structure of stable alloy.
In addition, when alloy contains carbon, and carbon content is favourable when being preferably 0.05 atom % to 0.8 atom %.Equally, preferably with the interpolation of above-mentioned additive boron bonded carbon, form stable crystallization, it also helps the stable of the mechanical hardening of alloy and structure.
In addition, purpose of the present invention realizes that by a kind of member this member is made by alloy according to the present invention.For fear of repetition, please refer to above-mentioned specifying.
Description of drawings
The present invention is subsequently under the situation that does not limit total inventive concept, carry out exemplary description according to embodiment and with reference to appended synoptic diagram, in addition, the present invention is with reference to relevant with public publication, further do not explain in this application according to all details of the present invention.Illustrate:
The sem photograph of Fig. 1 ingot casting, this ingot casting is made of alloy Ti-45Al-8Nb-0.2C (atom %);
Fig. 2 a-2c is after the diverse ways step, by each image of structure among the alloy Ti-45Al-8Nb-0.2C (atom %) of scanning electron microscope;
Fig. 3 a and 3b after the diverse ways step, each image of structure in alloy Ti-45Al-5Nb-2Mo according to the present invention (atom %), and
Pressure-extension curve the figure of Fig. 4 alloy Ti-45Al-5Nb-2Mo (atom %) sample.
Embodiment
Figure 1 illustrates two width of cloth figure of the structure in alloy Ti-45Al-8Nb-0.2C (atom %) ingot casting.These figure and following all figure take by the back scattered electron in scanning electron microscope.
That structure (Fig. 1) illustrates is α
2-mutually and γ-mutually lamella accumulation area, this lamella accumulation area are by previous γ-thin slice generation.This previous γ-thin slice is isolated from the particle band of the light tone formation of β-phase or B2-phase.α-the thin slice that at first forms in β-α-transformation further is being divided into α under the cooling
2-thin slice and γ-thin slice.
Other images of the structure of alloy Ti-45Al-8Nb-0.2C under scanning electron microscope image have been shown after the diverse ways step in 2c at Fig. 2 a.Shown in Fig. 2 a is on 1230 ℃ of following structures after the extruding.The direction of extrusion is level.This structure shows α
2-mutually with the particle of γ-mutually, wherein, the β of body-centred cubic-disappeared mutually.
Fig. 2 b shows the structure of the alloy after extruding under 1230 ℃ and another forging step under 1100 ℃.This structure shows α
2-mutually and γ-mutually particle and some a spot of α
2/ γ-lamella accumulation area.
In Fig. 2 c, illustrated 1230 ℃ of following extruding backs and subsequently at 1330 ℃ of heat treated alloy structures down.This structure also shows α
2-mutually with the particle of γ-mutually.This image shows has α
2-mutually with the full sheet structure of the lamella of γ-mutually.Lamella accumulation area size amounts to about 200 μ m, wherein, obvious accumulation area greater than 200 μ m also occurred.
As in the structure as shown in Fig. 2 a, also body-centred cubic no longer appears mutually in Fig. 2 b and the structure shown in the 2c.Therefore, the β in this temperature range-heat-treating after the extruding on thermodynamics is unsettled.
In Fig. 3 a and 3b, there is shown according to alloy structure of the present invention in two width of cloth scanning electron microscope.Based on alloy Ti-45Al-5Nb, add the molybdenum alloy element of 2 atom %.This alloy Ti-45Al-5Nb-2Mo that forms is based on a kind of moiety, as it described in European patent EP 1 015 650 B1.
Fig. 3 a and 3b show this according to alloy structure of the present invention, and this alloy structure is 1250 ℃ of down extruding and (Fig. 3 a) and observed after (Fig. 3 b) thermal treatment under 1270 ℃ at 1030 ℃ subsequently.
Structure in Fig. 3 a shows α
2-phase, γ-phase and the β that constitutes with light color and arrange with ribbon-mutually.Structure in Fig. 3 b shows α
2The particle of-phase and the γ-lamella accumulation area mutually and the β-phase of light color formation, γ-from crystallizing out (separating out) here again.
Structure among Fig. 3 a and the 3b is meticulous, very uniform, and this structure shows the uniform distribution of β-phase.The spheric structure appears after 1030 ℃ of following thermal treatment, wherein, when 1270 ℃ down heat treated materials have equally distributed β-(phase) particle and during for very even, complete flaky structure (Fig. 3 b), the banded β-phase particle and the direction of extrusion are arranged in parallel, and (Fig. 3 a).
The accumulation area size of the structure of alloy Ti-45Al-5Nb-2Mo amounts between 20 to 30 μ m, and littler 5 times than the full sheet structure of γ-titanium aluminum alloy at least.In addition, in that β-γ-phase is separated out in inside mutually, so that β-size distribution is very fine.Therefore, totally reached very fine and uniform structure.
Show that in test this meticulous and uniform structural form exists after reaching 1320 ℃ the thermal treatment of whole high temperature range.Thereby clearly demonstrate this structure, promptly surpass whole, for manufacturing process relevant temperature scope, exist the volume of enough β-phases to form, and suppressed the particulate increase effectively.
In the tension test that material is implemented, this material is heat-treated under 1030 ℃, and the extension limit that at room temperature records is 867MPa, and tensile strength is that 816MPa and plasticity maximum elongation amount are 1.8%.
Fig. 4 shows the pressure-stress strain curve of the alloy Ti-45Al-5Nb-2Mo sample that records in tension test.Specimen material is extruded under 1250 ℃ and subsequently 1030 ℃ of thermal treatments 2 hours, carries out the stove internal cooling then.The stress strain curve that obtains when 700 ℃ and 900 ℃ demonstrates, and this alloy is suitable for multiple high temperature and uses.
Reach very uniform microtexture in the alloy by adding a spot of molybdenum alloy element, make this alloy to use as high-temperature material well.
In addition, figure 4 illustrates at room temperature the result that (25 ℃) carry out tension test to material according to the invention, wherein, provided the curve of tensile pressures σ (MPa) corresponding to extension ε (%).Wherein, find that the extension limit has increased, and this extension limit increase in γ-titanium aluminum alloy was not observed also up to now.This has represented a kind of sign for meticulous especially and uniform structure.The increase of extension ultimate shows that this material can respond to partial pressure by plastic flow, and this is very favorable for ductility and damage deviation.
Variation according to temperature in the homogeneity of alloy of the present invention and the relevant technological temperature scope or composition is relevant, and this variation is avoidable technically.
Titanium aluminum alloy according to the present invention is to use casting metallurgy or powder metallurgy technology manufacturing.For example can process according to alloy of the present invention by forge hot, hot pressing or hot extrusion and hot rolling.
The present invention shows following advantage, although group of alloys namely occurred in industrial production Become and the variation of process conditions, still more effectively provide than up to now method to have Very uniform microstructure and high-intensity titanium-aluminium alloy.
Titanium-aluminium alloy according to the present invention has reached until under 700 ℃ to 800 ℃ the temperature Ductility under high strength and the good room temperature. Therefore, this alloy is applicable to multiple neck Territory, and for example can being applied in the member of specific high capacity, perhaps can for Use under the very high temperature of titanium-aluminium alloy.
Claims (5)
1. one kind by using the titanium aluminium base alloy that fusion metallurgy technology and powder metallurgy technology are made, described alloy has the alloy composition of Ti-zAl-yNb, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, and 5 atom %≤y≤10 atom %, it is characterized in that described alloy contains the molybdenum (Mo) of 0.1 atom % to 3 atom %.
2. one kind by using the titanium aluminium base alloy that fusion metallurgy technology and powder metallurgy technology are made, described alloy has the alloy composition of Ti-zAl-yNb-xB, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom % and 0.05 atom %≤x≤0.8 atom % is characterized in that, described alloy contains the molybdenum (Mo) of 0.1 atom % to 3 atom %.
3. one kind by using the titanium aluminium base alloy that fusion metallurgy technology and powder metallurgy technology are made, described alloy has the alloy composition of Ti-zAl-yNb-wC, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, and 5 atom %≤y≤10 atom % and 0.05 atom %≤w≤0.8 atom %, it is characterized in that described alloy contains the molybdenum (Mo) of 0.5 atom % to 3 atom %.
4. one kind by using the titanium aluminium base alloy that fusion metallurgy technology and powder metallurgy technology are made, described alloy has the alloy composition of Ti-zAl-yNb-xB-wC, wherein, 44.5 atom %≤z≤47 atom %, be preferably 44.5 atom %≤z≤45.5 atom %, 5 atom %≤y≤10 atom %, 0.05 atom %≤x≤0.8 atom % and 0.05 atom %≤w≤0.8 atom %, it is characterized in that described alloy contains the molybdenum (Mo) of 0.1 atom % to 3 atom %.
5. member, described member is by making according to each described alloy in the claim 1 to 4.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102004056582.1 | 2004-11-23 | ||
| DE102004056582A DE102004056582B4 (en) | 2004-11-23 | 2004-11-23 | Alloy based on titanium aluminides |
| PCT/EP2005/009402 WO2006056248A1 (en) | 2004-11-23 | 2005-09-01 | Titanium aluminide based alloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101056998A true CN101056998A (en) | 2007-10-17 |
| CN101056998B CN101056998B (en) | 2010-10-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2005800390124A Expired - Fee Related CN101056998B (en) | 2004-11-23 | 2005-09-01 | Titanium Aluminum Alloy |
Country Status (11)
| Country | Link |
|---|---|
| US (2) | US20100015005A1 (en) |
| EP (1) | EP1819838B1 (en) |
| JP (3) | JP2008520826A (en) |
| KR (1) | KR101010965B1 (en) |
| CN (1) | CN101056998B (en) |
| AT (1) | ATE425272T1 (en) |
| CA (1) | CA2587237C (en) |
| DE (2) | DE102004056582B4 (en) |
| ES (1) | ES2322082T3 (en) |
| RU (1) | RU2370561C2 (en) |
| WO (1) | WO2006056248A1 (en) |
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| CN101457314B (en) * | 2007-12-13 | 2013-07-24 | Gkss-盖斯特哈赫特研究中心有限责任公司 | Titanium aluminide alloys |
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| US5213635A (en) * | 1991-12-23 | 1993-05-25 | General Electric Company | Gamma titanium aluminide rendered castable by low chromium and high niobium additives |
| DE4224867A1 (en) * | 1992-07-28 | 1994-02-03 | Abb Patent Gmbh | Highly heat-resistant material |
| JPH06116691A (en) * | 1992-10-05 | 1994-04-26 | Mitsubishi Materials Corp | TiAl intermetallic compound Ti alloy heat treatment method |
| JPH06116692A (en) * | 1992-10-05 | 1994-04-26 | Honda Motor Co Ltd | TiAl intermetallic compound excellent in high temperature strength and method for producing the same |
| US5328530A (en) * | 1993-06-07 | 1994-07-12 | The United States Of America As Represented By The Secretary Of The Air Force | Hot forging of coarse grain alloys |
| GB9419712D0 (en) * | 1994-09-30 | 1994-11-16 | Rolls Royce Plc | A turbomachine aerofoil and a method of production |
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| US5653828A (en) * | 1995-10-26 | 1997-08-05 | National Research Council Of Canada | Method to procuce fine-grained lamellar microstructures in gamma titanium aluminides |
| DE19748874C2 (en) * | 1996-11-09 | 2000-03-23 | Max Planck Inst Eisenforschung | Use of a TiAl alloy |
| DE19735841A1 (en) * | 1997-08-19 | 1999-02-25 | Geesthacht Gkss Forschung | Titanium aluminide alloy contains niobium |
| US6174387B1 (en) * | 1998-09-14 | 2001-01-16 | Alliedsignal, Inc. | Creep resistant gamma titanium aluminide alloy |
| DE10058155A1 (en) * | 2000-11-22 | 2002-05-23 | Geesthacht Gkss Forschung | Alloy based on titanium aluminides produced using a smelting and powder metallurgical process and containing an alloy composition made from titanium, aluminum and niobium has specified an aluminum content |
| AT5199U1 (en) * | 2001-07-19 | 2002-04-25 | Plansee Ag | MOLDED PART FROM AN INTERMETALLIC GAMMA-TI-AL MATERIAL |
-
2004
- 2004-11-23 DE DE102004056582A patent/DE102004056582B4/en not_active Expired - Fee Related
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2005
- 2005-09-01 RU RU2007123588/02A patent/RU2370561C2/en not_active IP Right Cessation
- 2005-09-01 JP JP2007541707A patent/JP2008520826A/en active Pending
- 2005-09-01 DE DE502005006844T patent/DE502005006844D1/en not_active Expired - Lifetime
- 2005-09-01 EP EP05784793A patent/EP1819838B1/en not_active Expired - Lifetime
- 2005-09-01 AT AT05784793T patent/ATE425272T1/en active
- 2005-09-01 CN CN2005800390124A patent/CN101056998B/en not_active Expired - Fee Related
- 2005-09-01 CA CA2587237A patent/CA2587237C/en not_active Expired - Fee Related
- 2005-09-01 WO PCT/EP2005/009402 patent/WO2006056248A1/en not_active Ceased
- 2005-09-01 ES ES05784793T patent/ES2322082T3/en not_active Expired - Lifetime
- 2005-09-01 KR KR1020077014345A patent/KR101010965B1/en not_active Expired - Fee Related
-
2007
- 2007-05-21 US US11/805,043 patent/US20100015005A1/en not_active Abandoned
-
2008
- 2008-12-04 JP JP2008309663A patent/JP2009097095A/en active Pending
-
2009
- 2009-07-27 JP JP2009174427A patent/JP4467637B2/en not_active Expired - Fee Related
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2012
- 2012-06-28 US US13/536,281 patent/US20120263623A1/en not_active Abandoned
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101457314B (en) * | 2007-12-13 | 2013-07-24 | Gkss-盖斯特哈赫特研究中心有限责任公司 | Titanium aluminide alloys |
| CN101948967A (en) * | 2010-09-30 | 2011-01-19 | 洛阳双瑞精铸钛业有限公司 | TiAl-based alloy material with excellent high-temperature property and preparation method thereof |
| CN103409660A (en) * | 2013-08-12 | 2013-11-27 | 南京理工大学 | Novel Beta/Gamma-TiAl alloy with ultra-fine grain |
| CN103834844A (en) * | 2014-03-12 | 2014-06-04 | 北京工业大学 | V and Mn alloyed beta-phase solidified high Nb-TiAl alloy and preparation method thereof |
| CN104928531A (en) * | 2015-05-12 | 2015-09-23 | 哈尔滨工业大学 | Uniform TiAl alloy lamellar structure and preparation method thereof |
| CN109312427A (en) * | 2016-09-02 | 2019-02-05 | 株式会社Ihi | TiAl alloy and its manufacturing method |
| US11078563B2 (en) | 2016-09-02 | 2021-08-03 | Ihi Corporation | TiAl alloy and method of manufacturing the same |
| CN107699738A (en) * | 2017-09-29 | 2018-02-16 | 成都露思特新材料科技有限公司 | A kind of fine-grained TiAl alloy and preparation method thereof, aero-engine, automobile |
| CN116607048A (en) * | 2022-02-09 | 2023-08-18 | 中国科学院金属研究所 | Gamma-TiAl alloy for precision casting and preparation method thereof |
| CN120243935A (en) * | 2025-05-30 | 2025-07-04 | 西安欧中材料科技股份有限公司 | A titanium-aluminum alloy blade with a service temperature of 850°C and its preparation method and application |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1819838B1 (en) | 2009-03-11 |
| ES2322082T3 (en) | 2009-06-16 |
| CA2587237A1 (en) | 2006-06-01 |
| JP2009097095A (en) | 2009-05-07 |
| DE102004056582A1 (en) | 2006-06-01 |
| EP1819838A1 (en) | 2007-08-22 |
| ATE425272T1 (en) | 2009-03-15 |
| KR20070086597A (en) | 2007-08-27 |
| JP2009256802A (en) | 2009-11-05 |
| DE502005006844D1 (en) | 2009-04-23 |
| DE102004056582B4 (en) | 2008-06-26 |
| KR101010965B1 (en) | 2011-01-26 |
| RU2370561C2 (en) | 2009-10-20 |
| JP2008520826A (en) | 2008-06-19 |
| US20120263623A1 (en) | 2012-10-18 |
| RU2007123588A (en) | 2008-12-27 |
| CA2587237C (en) | 2012-03-20 |
| WO2006056248A1 (en) | 2006-06-01 |
| CN101056998B (en) | 2010-10-13 |
| US20100015005A1 (en) | 2010-01-21 |
| JP4467637B2 (en) | 2010-05-26 |
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