WO2010031985A1 - PROCEDE POUR LA FABRICATION D'UNE PIECE EN TITANE AVEC FORGEAGE INITIAL DANS LE DOMAINE β - Google Patents
PROCEDE POUR LA FABRICATION D'UNE PIECE EN TITANE AVEC FORGEAGE INITIAL DANS LE DOMAINE β Download PDFInfo
- Publication number
- WO2010031985A1 WO2010031985A1 PCT/FR2009/051786 FR2009051786W WO2010031985A1 WO 2010031985 A1 WO2010031985 A1 WO 2010031985A1 FR 2009051786 W FR2009051786 W FR 2009051786W WO 2010031985 A1 WO2010031985 A1 WO 2010031985A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- temperature
- forging
- alloy
- transus
- final
- Prior art date
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/25—Manufacture essentially without removing material by forging
-
- 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 manufacturing a titanium alloy component. It relates more particularly to a process comprising
- Titanium alloys are used in advanced applications, such as aeronautical turbines, to make certain parts subject to high stress and high temperatures. Pure titanium exists in two crystallographic forms: the ⁇ , hexagonal phase, which exists at ambient temperature, and the centric cubic ⁇ phase, which exists above the temperature called ⁇ -transus (or ⁇ transus), which is equal to 883 0 C for pure titanium.
- ⁇ -transus or ⁇ transus
- the ⁇ phase consists of a mixture of ⁇ phase and ⁇ phase.
- the alloy elements have the effect in particular of varying the ⁇ -transus temperature around 883 ° C.
- the development of a titanium alloy having the desired properties includes selecting alloying elements, and choosing the thermomechanical treatment undergone by the alloy.
- the alloy is therefore in the ⁇ -phase above the ⁇ -transus temperature, and respectively in a state of equilibrium between ⁇ and ⁇ phases or essentially ⁇ at room temperature.
- domain ⁇ is the temperature zone above the ⁇ -transus temperature
- ⁇ domain is the temperature zone immediately below the ⁇ -transus temperature in which the ⁇ -phases are and ⁇ are in equilibrium.
- a current manufacturing process for forgings made of titanium alloys comprises, for example, several forging passes which are all carried out in the ⁇ domain (the temperatures Ti and T 2 are therefore in this case less than the ⁇ -transus temperature).
- Such forging range does not allow complete recrystallization and refinement of the macrostructure.
- a nodule colony ⁇ is a group of several nodules having a preferred crystallographic orientation. These colonies help to reduce the fatigue strength of the room.
- Another manufacturing process for forgings made of titanium alloys comprises several forging passes, these passes being made in the ⁇ domain, except the last pass which is carried out in the ⁇ domain (the temperature Ti is therefore in this case less than ⁇ -transus temperature, and the temperature T 2 is greater than the ⁇ -transus temperature). The latter goes to a higher temperature, allows easier formatting of the room.
- the present invention aims to remedy these disadvantages.
- the aim of the invention is to propose a process which makes it possible to obtain a titanium alloy part having a more homogeneous structure and better mechanical properties, in particular withstand fatigue.
- This object is achieved by virtue of the fact that the temperature Ti is greater than the temperature ⁇ -transus of the alloy, that the temperature T 2 is lower than the temperature ⁇ -transus, that the only heating of said part above the ⁇ -transus temperature is the heating at the temperature Ti, that the initial forging precedes said final forging, this initial forging being carried out as soon as the temperature of said part is substantially homogeneous, and that the quenching is carried out at a speed greater than 150 ° C / min.
- the high deformation rate of the part by forging at a sufficiently high temperature makes it possible to refine the microstructure (obtaining ⁇ grains of smaller size) and to erase the heredity of the part.
- the part consists of substantially equiaxed phase grains ⁇ , the part having not yet been deformed since it is the first forging (the thickness of the piece is at this stage substantially constant).
- Forging deforms these grains, which recrystallize into fine ⁇ grains.
- These small ⁇ -grains recrystallize themselves in fine-tuned ⁇ phase during quenching after forging.
- the workpiece does not include undesirable phase ⁇ nodules at room temperature. Soaking the part quickly enough and not to return later in the ⁇ domain keeps this fine microstructure, and prevent the grains from growing. As a result, the microstructure of the alloy is refined and more homogeneous. The holding of the piece to fatigue is improved.
- the background noise is decreased. Indeed, this background noise is generated by inhomogeneities in the microstructure.
- the structure being generally more homogeneous, it follows a decrease in background noise, and therefore a more fine and easier detection of metallurgical defects in the room.
- FIG. 2A is a photomicrograph of a titanium alloy heated below the ⁇ -transus temperature
- FIG. 2B is an enlargement of the photomicrograph of FIG. 2A
- FIG. 3A is a photomicrograph of a titanium alloy heated above the ⁇ -transus temperature
- FIG. 3B is an enlargement of the photomicrograph of FIG. 3A
- FIG. 4A is a photomicrograph of a titanium alloy heated above the ⁇ -transus temperature and then deformed with a strain rate of 1,
- FIG. 4B is a photomicrograph of a titanium alloy heated above the ⁇ -transus temperature and then deformed with a strain rate of 2.5.
- the method according to the invention generally applies to a billet obtained by one or more fusions of a titanium alloy, the casting of this alloy into an ingot, then a forging according to a given thermodynamic cycle.
- FIG. 1 shows in a diagram the steps of the method according to the invention for the manufacture of a titanium alloy part.
- the x-axis represents the increasing time t (without scale)
- the y-axis represents the temperature T in degrees Celsius, increasing from the ambient temperature T A
- the temperature of the part as a function of time t is represented on this diagram by a curve.
- step 1 the part is heated to a temperature Ti which is greater than the ⁇ -transus temperature for this alloy.
- the workpiece is maintained at this temperature Ti long enough so that the temperature of the workpiece is substantially homogeneous and equal to Ti (step 1-1). This temperature maintenance is illustrated by the plateau in step 1.
- FIG. 2A is a photograph taken under the microscope of a titanium alloy heated to a temperature just below the ⁇ -transus temperature, without forging (the ⁇ -transus temperature for this alloy is 1001 ° C.).
- Figure 2B is an enlargement of the area of Figure 2A surrounded by a white rectangle. Note in Figure 2B the presence in the alloy of oriented structures, in this case orientated fiberizations consisting of needles 10 (elongate grains) substantially parallel.
- FIG. 3A is a microscopic photograph of the same titanium alloy as that of FIG. 2A, which is heated to a temperature just above the ⁇ -transus temperature, without undergoing forging.
- Figure 3B is an enlargement of the area of Figure 3A surrounded by a white rectangle. It is found that after passing above the temperature of ⁇ -transus, the oriented fiberizations disappear and the structure is more isotropic. Indeed, as soon as the temperature of the alloy exceeds the ⁇ -transus temperature, there is a transformation of the ⁇ phase into ⁇ phase, which induces an equiaxial recrystallization of the microstructure with a grain magnification. The existing stresses in the room before heating above the ⁇ -transus temperature are largely erased. The macrostructure and the state of the alloy is therefore more suitable for undergoing the forging operation.
- the whole piece is at a temperature above the ⁇ -transus temperature during the forging operation, which is the case as soon as all the zones of the part are substantially at the temperature Ti.
- the part is then forged at a temperature substantially equal to Ti to give it an intermediate shape approximating its final shape (step 1-2).
- the deformation rate T d is defined as the logarithm of the ratio of the thickness H, of the part before deformation and of its thickness H f after deformation:
- this degree of deformation is greater than 1. Preferably it is greater than 1.6.
- a higher deformation rate leads to a greater refinement of the microstructure (reduction of the grain size), which improves the fatigue strength of the part.
- FIGS. 4A and 4B are microscopic photographs which show a T16242 alloy after forging in the ⁇ domain with a strain rate of 1 and a strain rate of 2.5 respectively. Tests carried out by the inventors on these samples reveal that the lifetime of such an alloy of T16242 goes from 78,000 cycles (at 772 MPa) for a deformation rate equal to 1, to 130,000 cycles for a deformation rate. equal to 2.5.
- the initial forging operation above should be performed using dies such that the shape of the workpiece after forging is as close as possible to the final shape of the workpiece, so as to minimize the stresses generated by the work. subsequent operation of final forging.
- care will be taken to use matrices of simple shape (for example frustoconical matrix, flat pile, or diabolo) so as to allow free flow of the material throughout the mold and to prevent material from being trapped. in cavities during the forging operation.
- the shape of the piece is of the diabolo or frustoconical type.
- step 1-3 the part undergoes quenching (step 1-3) from the temperature forging Ti up to room temperature at a speed above 150 ° C / min (degrees Celsius per minute).
- This rapid quenching makes it possible to maintain a fine microstructure of the part (fine grains) and thus to optimize the mechanical characteristics of the part, and in particular its elastic limit, as has been verified during mechanical tests carried out by the inventor .
- the quenching is carried out at a speed of between 200 and 400 ° C./min. Even more advantageously, the quenching is carried out at a speed substantially equal to 250 ° C./min, the tests carried out by the inventors having demonstrated that the mechanical characteristics were best optimized at this quenching speed.
- water quenching is carried out.
- the part is heated to a temperature T 2 lower than the ⁇ -transus temperature (which corresponds to step 2 in FIG. 1).
- T 2 the alloy is therefore in the ⁇ domain, and the microstructure of the alloy is not modified.
- the fiberization (pointed structure) made during the initial forging is therefore preserved.
- the method according to the invention may comprise one or more intermediate forging passes, all in the ⁇ domain (therefore at a temperature below the ⁇ -transus temperature), after the initial forging and before the final forging.
- the final forging may be followed by an income operation in the ⁇ domain.
- This income (step 3 in FIG. 1) in the ⁇ domain is therefore carried out at a temperature below the ⁇ -transus temperature.
- the part is heated to a temperature T 3 (step 3-1), then cooled without quenching (step 3-2) to room temperature .
- the temperature T 2 is approximately 1000 ° C.
- the temperature T 3 is 595 ° C.
- This income makes it possible to reduce the residual stresses generated in the part by the final forging operation.
- the titanium alloy used is an alloy of the family of ⁇ or quasi- ⁇ titanium.
- this alloy can be the
- TA6V or the T16242 (TA6Zr4DE). These alloys are for example used in aeronautical turbines.
- Tests carried out by the inventors on alloys T16242 show that a part obtained by a method according to the invention has better fatigue properties than a part obtained by a method according to the prior art.
- the part manufactured by a method as described above is for example an aeronautical turbine disk. This piece is for example an aeronautical turbine drum.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0919278A BRPI0919278A2 (pt) | 2008-09-22 | 2009-09-22 | processo para a fabricação de uma liga de titânio |
JP2011527388A JP2012503098A (ja) | 2008-09-22 | 2009-09-22 | 初期β鍛造によってチタン部品を製造する方法 |
CA2738007A CA2738007A1 (fr) | 2008-09-22 | 2009-09-22 | Procede pour la fabrication d'une piece en titane avec forgeage initial dans le domaine .beta. |
US13/120,243 US20110240181A1 (en) | 2008-09-22 | 2009-09-22 | Method for manufacturing a titanium part through initial beta forging |
EP09748423A EP2346629A1 (fr) | 2008-09-22 | 2009-09-22 | Procede pour la fabrication d'une piece en titane avec forgeage initial dans le domaine |
CN2009801467009A CN102223964A (zh) | 2008-09-22 | 2009-09-22 | 通过初始β锻制造钛零件的方法 |
IL211876A IL211876A0 (en) | 2008-09-22 | 2011-03-22 | Method for manufacturing a titanium part through initial ?? forging |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0856339A FR2936173B1 (fr) | 2008-09-22 | 2008-09-22 | Procede pour la fabrication d'une piece en titane avec forgeage initial dans le domaine beta |
FR0856339 | 2008-09-22 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010031985A1 true WO2010031985A1 (fr) | 2010-03-25 |
Family
ID=40843267
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/051786 WO2010031985A1 (fr) | 2008-09-22 | 2009-09-22 | PROCEDE POUR LA FABRICATION D'UNE PIECE EN TITANE AVEC FORGEAGE INITIAL DANS LE DOMAINE β |
Country Status (10)
Country | Link |
---|---|
US (1) | US20110240181A1 (fr) |
EP (1) | EP2346629A1 (fr) |
JP (1) | JP2012503098A (fr) |
CN (1) | CN102223964A (fr) |
BR (1) | BRPI0919278A2 (fr) |
CA (1) | CA2738007A1 (fr) |
FR (1) | FR2936173B1 (fr) |
IL (1) | IL211876A0 (fr) |
RU (1) | RU2011115833A (fr) |
WO (1) | WO2010031985A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013034851A1 (fr) | 2011-09-05 | 2013-03-14 | Snecma | Procédé de préparation d'éprouvettes de caractérisation mécanique d'un alliage de titane |
RU2635595C1 (ru) * | 2016-09-23 | 2017-11-14 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | СПОСОБ ПОЛУЧЕНИЯ ДЕТАЛЕЙ ГАЗОТУРБИННЫХ ДВИГАТЕЛЕЙ ИЗ ТИТАНОВОГО ПСЕВДО -β - СПЛАВА С ЛИГАТУРОЙ Ti-Al-Mo-V-Cr-Fe |
RU2660461C1 (ru) * | 2017-04-25 | 2018-07-06 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | СПОСОБ ИЗГОТОВЛЕНИЯ ДЕТАЛЕЙ ИЗ ТИТАНОВЫХ ПСЕВДО - α - СПЛАВОВ |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2982279B1 (fr) * | 2011-11-08 | 2013-12-13 | Snecma | Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de |
NO2975028T3 (fr) * | 2013-03-15 | 2018-07-21 | ||
US10604823B2 (en) * | 2013-06-05 | 2020-03-31 | Kobe Steel, Ltd. | Forged titanium alloy material and method for producing same, and ultrasonic inspection method |
CN107824731B (zh) * | 2017-09-28 | 2019-04-26 | 湖南金天钛业科技有限公司 | 一种Ti55钛合金大规格棒材锻造方法 |
CN109234568B (zh) * | 2018-09-26 | 2021-07-06 | 西部超导材料科技股份有限公司 | 一种Ti6242钛合金大规格棒材的制备方法 |
CN112222341A (zh) * | 2020-10-16 | 2021-01-15 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Tc17钛合金模锻件的制造方法 |
CN113182476B (zh) * | 2021-04-28 | 2023-10-13 | 西部钛业有限责任公司 | 一种高强tc11钛合金锻件的制备方法 |
CN114346141A (zh) * | 2022-01-17 | 2022-04-15 | 太原理工大学 | 一种制备弱α织构钛合金锻件的多段热加工方法 |
CN117000926B (zh) * | 2023-08-10 | 2024-04-12 | 陕西鼎益科技有限公司 | 一种提高钛合金棒材组织均匀性的锻造成型方法 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2653449A1 (fr) * | 1989-10-23 | 1991-04-26 | Cooper Ind Inc | Piece en alliage a base de titane et procede de production de celle-ci. |
US5795413A (en) * | 1996-12-24 | 1998-08-18 | General Electric Company | Dual-property alpha-beta titanium alloy forgings |
US5861070A (en) * | 1996-02-27 | 1999-01-19 | Oregon Metallurgical Corporation | Titanium-aluminum-vanadium alloys and products made using such alloys |
EP1136582A1 (fr) * | 2000-03-24 | 2001-09-26 | General Electric Company | Traitement d'une billette en alliage de titane pour ameliorer l'abilité d'inspection par ultrasons |
US20040035509A1 (en) * | 2002-08-26 | 2004-02-26 | Woodfield Andrew Philip | Processing of alpha-beta titanium alloy workpieces for good ultrasonic inspectability |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5201894A (en) * | 1992-03-27 | 1993-04-13 | United Technologies Corporation | Balanced force workpiece location means |
FR2839727B1 (fr) * | 2002-05-14 | 2004-06-25 | Technologica Sarl | Procede d'elaboration et de mise en forme de pieces en fonte a graphite spheroidal a caracteristiques mecaniques elevees |
GB0300999D0 (en) * | 2003-01-16 | 2003-02-19 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
US7370787B2 (en) * | 2003-12-15 | 2008-05-13 | Pratt & Whitney Canada Corp. | Compressor rotor and method for making |
CN1329549C (zh) * | 2005-10-26 | 2007-08-01 | 北京科技大学 | 一种细化TiAl合金铸锭显微组织的热加工工艺 |
CN101130840A (zh) * | 2007-09-27 | 2008-02-27 | 上海交通大学 | 原位自生钛基复合材料的渗氢超塑性加工方法 |
-
2008
- 2008-09-22 FR FR0856339A patent/FR2936173B1/fr active Active
-
2009
- 2009-09-22 RU RU2011115833/02A patent/RU2011115833A/ru not_active Application Discontinuation
- 2009-09-22 EP EP09748423A patent/EP2346629A1/fr not_active Withdrawn
- 2009-09-22 WO PCT/FR2009/051786 patent/WO2010031985A1/fr active Application Filing
- 2009-09-22 CN CN2009801467009A patent/CN102223964A/zh active Pending
- 2009-09-22 CA CA2738007A patent/CA2738007A1/fr not_active Abandoned
- 2009-09-22 BR BRPI0919278A patent/BRPI0919278A2/pt not_active IP Right Cessation
- 2009-09-22 US US13/120,243 patent/US20110240181A1/en not_active Abandoned
- 2009-09-22 JP JP2011527388A patent/JP2012503098A/ja not_active Withdrawn
-
2011
- 2011-03-22 IL IL211876A patent/IL211876A0/en unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2653449A1 (fr) * | 1989-10-23 | 1991-04-26 | Cooper Ind Inc | Piece en alliage a base de titane et procede de production de celle-ci. |
US5861070A (en) * | 1996-02-27 | 1999-01-19 | Oregon Metallurgical Corporation | Titanium-aluminum-vanadium alloys and products made using such alloys |
US5795413A (en) * | 1996-12-24 | 1998-08-18 | General Electric Company | Dual-property alpha-beta titanium alloy forgings |
EP1136582A1 (fr) * | 2000-03-24 | 2001-09-26 | General Electric Company | Traitement d'une billette en alliage de titane pour ameliorer l'abilité d'inspection par ultrasons |
US20040035509A1 (en) * | 2002-08-26 | 2004-02-26 | Woodfield Andrew Philip | Processing of alpha-beta titanium alloy workpieces for good ultrasonic inspectability |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013034851A1 (fr) | 2011-09-05 | 2013-03-14 | Snecma | Procédé de préparation d'éprouvettes de caractérisation mécanique d'un alliage de titane |
RU2635595C1 (ru) * | 2016-09-23 | 2017-11-14 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | СПОСОБ ПОЛУЧЕНИЯ ДЕТАЛЕЙ ГАЗОТУРБИННЫХ ДВИГАТЕЛЕЙ ИЗ ТИТАНОВОГО ПСЕВДО -β - СПЛАВА С ЛИГАТУРОЙ Ti-Al-Mo-V-Cr-Fe |
RU2660461C1 (ru) * | 2017-04-25 | 2018-07-06 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | СПОСОБ ИЗГОТОВЛЕНИЯ ДЕТАЛЕЙ ИЗ ТИТАНОВЫХ ПСЕВДО - α - СПЛАВОВ |
Also Published As
Publication number | Publication date |
---|---|
US20110240181A1 (en) | 2011-10-06 |
FR2936173A1 (fr) | 2010-03-26 |
IL211876A0 (en) | 2011-06-30 |
CN102223964A (zh) | 2011-10-19 |
JP2012503098A (ja) | 2012-02-02 |
FR2936173B1 (fr) | 2012-09-21 |
RU2011115833A (ru) | 2012-10-27 |
EP2346629A1 (fr) | 2011-07-27 |
CA2738007A1 (fr) | 2010-03-25 |
BRPI0919278A2 (pt) | 2015-12-15 |
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