WO2010031982A1 - Procede de forgeage d'une piece thermomecanique en alliage de titane. - Google Patents
Procede de forgeage d'une piece thermomecanique en alliage de titane. Download PDFInfo
- Publication number
- WO2010031982A1 WO2010031982A1 PCT/FR2009/051780 FR2009051780W WO2010031982A1 WO 2010031982 A1 WO2010031982 A1 WO 2010031982A1 FR 2009051780 W FR2009051780 W FR 2009051780W WO 2010031982 A1 WO2010031982 A1 WO 2010031982A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- forging
- blank
- billet
- deformation
- beta
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/04—Shaping in the rough solely by forging or pressing
-
- 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
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
-
- 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
- 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 invention relates to a method of forging a thermomechanical part made of a titanium beta or alpha / beta alloy.
- the invention also relates to a method of manufacturing a thermomechanical part comprising this forging process.
- thermomechanical part resulting from this forging process or manufacturing method, said thermomechanical part being an alpha / beta beta forged alloy forging having a fine and homogeneous microstructure with a grain size of 1 ⁇ m. order of 50 to 100 ⁇ m.
- the invention also relates to a turbomachine comprising such a thermomechanical part.
- the invention applies particularly, but not exclusively, to rotating parts of turbomachines, such as disks, journals and wheels, and in particular to high-pressure compressor discs, especially to DAMs (monobloc bladed disks).
- rotating parts typically have a thickness greater than 10 mm, or even 20 or 30 mm.
- the present invention relates to all types of titanium alloy stabilized in temperature: titanium alloys of the beta and alpha / beta classes (here we speak of the structure of the finished part).
- the present invention particularly relates to titanium alloys designated "alpha / beta forged beta", the word “alpha / beta” corresponding to the microstructure of the part, namely with coexistence of alpha and beta titanium phases, this piece being put shaped by forging.
- the forging process comprises in particular a final step of deformation by stamping in the beta domain of the titanium alloy.
- beta domain of the titanium alloy corresponds to temperatures above the temperature of beta transus Tp, the temperatures below the temperature of beta transus Tp corresponding to the alpha / beta domain.
- the forging process corresponds to the diagram of Figure 1, described below. Initially, a titanium alloy ingot obtained by melting is converted into a biilette having any desired shape, which is most of the time a cylindrical shape.
- Such a biilette constitutes a half-product and is obtained by one or more fusions of the parent alloy and then the casting of an ingot itself forged according to a precise thermomechanical cycle (which does not correspond to the forging process according to the present invention ), in order to reduce the section of the ingot and obtain the biilette with controlled metallurgical and dimensional characteristics.
- the fusion or fusions are carried out according to one of the following techniques: vacuum arc remelting ("VAR" for "Vacuum Arc Remelting"), beam remelting of electrons in a cold crucible (" EBCHR “for” Electron Beam CoId Heart Remelting ”) or by the Plasma Arc Melting (" PAM ”) technique.
- This biilette is then subjected to the forging process illustrated in FIG. 1 according to a plot of the temperature to which the biilette is subjected as a function of time.
- a first forging step is carried out, generally but not systematically, consisting of one or more intermediate forging or "rough forging".
- the biilette is first heated (reference a) between moments to and ti from the ambient temperature T 0 to the temperature Ti lower than the temperature of beta transus Tp.
- this temperature Ti is of the order of the temperature of beta transus T ⁇ - 60 0 C and this rise in temperature, depending on the massiveness of the biilette, takes, for example, about 2 hours for a biilette of a diameter 200 mm.
- the twin is held at the temperature Ti (mark b) between moments tj . and t 2 , corresponding to a duration of about 1 hour or more, to ensure that all the material constituting the biilette has reached this temperature Ti, before proceeding to the actual forging operation (reference c ), that is to say to the hot plastic deformation by press (milling), pestle, rolling mill ... of the twin between moments h. and t 3 , corresponding to a duration of a few tens of seconds, thereby forming a blank.
- the blank being in the open air, it follows a natural cooling of a few tens of 0 C of the surface of the room, while the heart of the room is cooled a little or warms of some 0 C depending on the massiveness of the part and the forging conditions, in particular the rate of deformation.
- the blank (mark d) is allowed to cool to room temperature To, between moments t 3 and U 1 corresponding to a duration of approximately a few tens of minutes. From the moment t 4 , either the blank is left at the ambient temperature To until the moment tn from which the second stage of forging or final forging starts, or a second or several other forging (s) is carried out ( s) (marks a ', b', c ', d' for a second blank forging) similar to the first rough forging (marks a, b, c, d) described previously.
- an alternative is to start earlier a second blank forging by heating (mark e) the blank between the times t 3 and t * of the first forging blank, ie not to wait for complete cooling up to the ambient temperature To of the blank (mark d of the first blank forging).
- the second blank forging is started by resuming the rise in temperature of the blank (reference e) to the temperature Ti and then continuing with a temperature maintenance (reference b 1 ) preceding the forging operation properly
- This alternative makes it possible to reduce the implementation time of the forging process without risking changing the microstructure of the billet during a complete cooling and a subsequent rise in temperature (d and ao marks).
- the second stage of forging or final forging which starts at the moment tn, it takes steps similar to those of the rough forging except for the value of the temperature at which is carried the blank before performing the actual forging operation, since it is the temperature T 2 greater than the temperature of beta transus Tp.
- this temperature T 2 is of the order of the temperature of beta transus Tp + 25 ° C.
- the final forging comprises a heating of the blank (mark A) between the moments tn and tn + i from the ambient temperature To to the temperature T 2 , then a temperature maintenance T 2 (reference B) between the moments tn + i and W, before proceeding to the actual forging operation (reference C) of the blank between the moments tn +2 and tn +3 .
- This forging operation (C mark) of the blank is performed at the temperature T 2 , in the beta domain (temperature greater than T ⁇ ), the progressive cooling of the blank during this forging operation possibly leading to a part of the blank subjected to the forging operation has a temperature less than T ⁇ and is therefore also forged at a temperature corresponding to the alpha / beta domain.
- the forged part thus obtained (reference D), called forged blank piece or forged part, is cooled down to the ambient temperature T 0 between the moments tn + 3 and tn + 4.
- the other forging parameters forging and final forging steps including forging speed, transfer time between the furnace and forging equipment, transfer time between forging equipment and the part cooling system After forging are defined according to the geometry and the massiveness of the part on the one hand and the industrial equipment available on the other hand.
- the number of forging roughing as well as the characteristics of each forging operation proper (c, c ', ... C marks) of the forging and final forging stages in particular the choice of the forging equipment (hydraulic press , mechanical screw press, pestle, rolling mill), the position of the billet / blank with respect to the forging tool, the level of stress exerted and the duration, as well as the number of repetitions are defined for each type of piece, according to its geometry and massiveness, according to a pre-established procedure for progressively deforming the billet and the blank by forming, at the end of the process forging, a forging with the required geometrical characteristics.
- a forged piece forming a product that can be described as a finished product is obtained in that this product is then no longer subject to subsequent forging and / or plastic deformation operations. ; this product will then be machined and undergo further processing, including surface conditioning according to its characteristics of use, especially within the engine forming the turbomachine.
- the billet of titanium alloy subjected to the forging process described above initially has heterogeneous microstructures.
- a microstructure containing one or more large grains of titanium which may have a size of up to several millimeters, or even of the order of a centimeter, especially titanium beta phase.
- These large grains not recrystallized into smaller grains, form isolated islands which, because of their large size, are not refined, that is to say transformed into smaller recrystallized grains by the forging process described above.
- the present invention aims to provide a forging process to overcome the disadvantages of the prior art and in particular offering the possibility of removing in the blank any presence of heterogeneous microstructures and in particular of a possible presence of large grains in the starting billet, to provide a homogeneous microstructure of the forged part.
- the present invention relates to a forging process of a thermomechanical part in titanium beta or alpha / beta alloy, comprising the following steps:
- a billet made of a titanium alloy having a temperature of beta transus Tp is provided; at least one forging step is carried out of said billet, in which said billet is heated to a temperature Ti lower than the temperature of beta transus Tp before performing the actual forging operation during which said billet is subjected to plastic deformation, which results in a blank, and then allowed to cool the blank;
- a final forging step of said blank is carried out, in which said blank is heated to a temperature T 2 greater than the temperature of beta transus Tp before performing the actual forging operation during which said blank undergoes a deformation plastic, which leads to a forged part and then the cooling of the forged part.
- the method is characterized in that said forging operation of the blank forging step performs at all points of said billet a local deformation greater than a minimum rate of deformation.
- deformation rate here is meant the cumulative plastic deformation at a point in the part, also called equivalent deformation, which is therefore considered on the part having undergone the forging operation blank considered. It is therefore a question of carrying out during the blank forging step
- the solution according to the present invention amounts to modifying the deformation conditions imposed on the billet during the forging process at the time of the actual forging operation (reference c and / or c ') of at least one of the rough forging steps, i.e. for the forging operation (s) performed in the alpha / beta domain, ie below the beta transus temperature Tp.
- the solution according to the invention on the one hand applies during the rough forging step, and not during the final forging step, and on the other hand is based on a local minimum deformation, and not on a minimum overall deformation of the part.
- the applicant has found that the final forging step does not allow, and this regardless of the local deformation rate achieved, to produce fine and homogeneous microstructures, especially if the blank (or the billet) has beforehand a heterogeneous microstructure, in particular an isolated large grain microstructure.
- a minimum deformation rate is expected from the actual forging operation of the rough forging step of at least 0.2, preferably said minimum deformation ratio is 0.3 and preferably 0.4.
- said minimum local deformation has indeed taken place at any point of the billet by means of numerical simulation computer tools of the actual forging operation.
- the process relates to an alpha-beta titanium alloy.
- one of the two following alloys is preferably used:
- Ti 6242 the titanium alloy called "Ti 6242” or Ti-6Al-2Sn-4Zr-2Mo, which comprises about 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum (alloy TA6Zr4DE according to the metallurgical nomenclature),
- Ti 17 or TACD4 or " H-5AL-4Mo-4Cr-2Sn-2Zr, which comprises approximately 5% aluminum, 4% molybdenum, 4% chromium, 2% of tin, and 2% zirconium.
- FIGS. 2 and 3 respectively show microstructure photographs corresponding to the situation preceding the production of the forging process according to the invention, and the modified microstructure resulting from the forging process according to the invention.
- Figure 2 there is a very large grain nonrecrystallized beta phase, a size of the order of 20 x 8 mm observed on billets.
- a forging process has been carried out comprising a single blank forging step in which, for this blank forging step, said forging operation performs at all points of said billet a deformation greater than a minimum deformation rate equal to 0.3.
- FIG. 3 shows that the very large beta-phase grain has recrystallized well since it results in a homogeneous, fine microstructure, namely a grain size of the order of 50 to 100 ⁇ m.
- thermomechanical part obtained is a forged beta / alpha / beta alloy forgone which has a finer or finer microstructure with respect to the microstructure of the starting billet.
- the fine microstructure obtained having a typical grain size of the order of a few hundred micrometers at most.
- a forging process comprising at least two rough forging steps, having made it possible for at least two successive forging stages to be forged, said forging operation performs at all points of said billet a deformation greater than a minimum strain rate equal to 0.2; or - a forging process comprising at least a first and a second rough forging step and in which, for one of the first and the second blank forging step, said forging operation performs at all points of said billet a deformation greater than a minimum strain rate of 0.3; or - a forging process comprising at least two rough forging steps and wherein, for each rough forging step, said forging operation performs at all points of said billet a deformation greater than a minimum deformation rate equal to 0.2 .
- two, three, four or more blank forging steps can be provided.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (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 |
---|---|---|---|
EP09748827.4A EP2344290B1 (fr) | 2008-09-22 | 2009-09-22 | Procede de forgeage d'une piece thermomecanique en alliage de titane. |
CA2737412A CA2737412A1 (fr) | 2008-09-22 | 2009-09-22 | Procede de forgeage d'une piece thermomecanique en alliage de titane |
JP2011527386A JP2012502803A (ja) | 2008-09-22 | 2009-09-22 | チタン合金熱機械的部品の鍛造方法 |
CN200980137246.0A CN102159340B (zh) | 2008-09-22 | 2009-09-22 | 一种锻造钛合金制造的热机械部件的方法 |
BRPI0919264A BRPI0919264A2 (pt) | 2008-09-22 | 2009-09-22 | processos de forjamento de uma peça termomecânica de liga de titânio beta ou alfa/beta, de fabricação de uma peça termomecânica feita de uma liga de titânio, peça termomecânica, e turbomáquina |
RU2011115813/02A RU2510680C2 (ru) | 2008-09-22 | 2009-09-22 | Способ ковки термомеханической детали, выполненной из титанового сплава |
US13/120,048 US20110192509A1 (en) | 2008-09-22 | 2009-09-22 | Method for forging a titanium alloy thermomechanical part |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FRFR0856337 | 2008-09-22 | ||
FR0856337A FR2936172B1 (fr) | 2008-09-22 | 2008-09-22 | Procede de forgeage d'une piece thermomecanique en alliage de titane |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010031982A1 true WO2010031982A1 (fr) | 2010-03-25 |
Family
ID=40821901
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/051780 WO2010031982A1 (fr) | 2008-09-22 | 2009-09-22 | Procede de forgeage d'une piece thermomecanique en alliage de titane. |
Country Status (9)
Country | Link |
---|---|
US (1) | US20110192509A1 (fr) |
EP (1) | EP2344290B1 (fr) |
JP (1) | JP2012502803A (fr) |
CN (1) | CN102159340B (fr) |
BR (1) | BRPI0919264A2 (fr) |
CA (1) | CA2737412A1 (fr) |
FR (1) | FR2936172B1 (fr) |
RU (1) | RU2510680C2 (fr) |
WO (1) | WO2010031982A1 (fr) |
Cited By (2)
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 |
CN114178453A (zh) * | 2021-11-04 | 2022-03-15 | 大冶特殊钢有限公司 | 一种高合金方坯的径向锻造方法 |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2469122C1 (ru) * | 2011-10-21 | 2012-12-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" | Способ термомеханической обработки заготовок из двухфазных титановых сплавов |
FR2982279B1 (fr) * | 2011-11-08 | 2013-12-13 | Snecma | Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de |
CN102517530B (zh) * | 2011-12-16 | 2013-09-11 | 陕西宏远航空锻造有限责任公司 | 一种提高Ti5553钛合金组织性能的热加工方法 |
JP6324736B2 (ja) * | 2014-01-23 | 2018-05-16 | 株式会社日立製作所 | 鍛造方法およびその装置 |
FR3024160B1 (fr) * | 2014-07-23 | 2016-08-19 | Messier Bugatti Dowty | Procede d'elaboration d`une piece en alliage metallique |
FR3027921A1 (fr) * | 2014-10-31 | 2016-05-06 | Snecma | Alliages a base de titane presentant des proprietes mecaniques ameliorees |
CN109722564A (zh) * | 2019-01-10 | 2019-05-07 | 青海聚能钛金属材料技术研究有限公司 | Ti-6242钛合金及其制备方法 |
CN109722565A (zh) * | 2019-01-10 | 2019-05-07 | 青海聚能钛金属材料技术研究有限公司 | 耐高温钛合金及其制备方法和应用 |
CN111842747B (zh) * | 2020-06-17 | 2022-07-22 | 西部超导材料科技股份有限公司 | 一种大规格ta15钛合金异形锻坯的锻造方法 |
CN113976658A (zh) * | 2021-10-22 | 2022-01-28 | 西部金属材料股份有限公司 | 一种超大规格钛合金管材的制备方法 |
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FR2475952A1 (fr) * | 1980-02-14 | 1981-08-21 | Rolls Royce | Procede de forgeage d'une piece en alliage a base de titane |
JPS58145323A (ja) * | 1982-02-22 | 1983-08-30 | Toshiba Corp | チタン合金の鍛造方法 |
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 |
EP1340832A1 (fr) * | 2002-03-01 | 2003-09-03 | Snecma Moteurs | Produits minces en alliages de titane bêta ou quasi bêta, fabrication par forgeage |
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JPS57202935A (en) * | 1981-06-04 | 1982-12-13 | Sumitomo Metal Ind Ltd | Forging method for titanium alloy |
JPH0289532A (ja) * | 1988-09-27 | 1990-03-29 | Sumitomo Metal Ind Ltd | チタン合金の恒温鍛造方法 |
JP3367392B2 (ja) * | 1997-08-28 | 2003-01-14 | 住友金属工業株式会社 | チタンスラブの製造方法 |
JP3559717B2 (ja) * | 1998-10-29 | 2004-09-02 | トヨタ自動車株式会社 | エンジンバルブの製造方法 |
US6884279B2 (en) * | 2002-07-25 | 2005-04-26 | General Electric Company | Producing metallic articles by reduction of nonmetallic precursor compounds and melting |
RU2229952C1 (ru) * | 2002-11-15 | 2004-06-10 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "Салют" | Способ штамповки заготовок из титановых сплавов |
US6754954B1 (en) * | 2003-07-08 | 2004-06-29 | Borgwarner Inc. | Process for manufacturing forged titanium compressor wheel |
RU2246556C1 (ru) * | 2004-01-22 | 2005-02-20 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Способ получения деформированной заготовки из титанового сплава и изделие, полученное из нее |
US20080035250A1 (en) * | 2006-08-09 | 2008-02-14 | United Technologies Corporation | Grain refinement of titanium alloys |
CN100567534C (zh) * | 2007-06-19 | 2009-12-09 | 中国科学院金属研究所 | 一种高热强性、高热稳定性的高温钛合金的热加工和热处理方法 |
-
2008
- 2008-09-22 FR FR0856337A patent/FR2936172B1/fr active Active
-
2009
- 2009-09-22 BR BRPI0919264A patent/BRPI0919264A2/pt not_active IP Right Cessation
- 2009-09-22 EP EP09748827.4A patent/EP2344290B1/fr active Active
- 2009-09-22 US US13/120,048 patent/US20110192509A1/en not_active Abandoned
- 2009-09-22 JP JP2011527386A patent/JP2012502803A/ja active Pending
- 2009-09-22 CN CN200980137246.0A patent/CN102159340B/zh active Active
- 2009-09-22 WO PCT/FR2009/051780 patent/WO2010031982A1/fr active Application Filing
- 2009-09-22 CA CA2737412A patent/CA2737412A1/fr not_active Abandoned
- 2009-09-22 RU RU2011115813/02A patent/RU2510680C2/ru active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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FR2475952A1 (fr) * | 1980-02-14 | 1981-08-21 | Rolls Royce | Procede de forgeage d'une piece en alliage a base de titane |
JPS58145323A (ja) * | 1982-02-22 | 1983-08-30 | Toshiba Corp | チタン合金の鍛造方法 |
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 |
EP1340832A1 (fr) * | 2002-03-01 | 2003-09-03 | Snecma Moteurs | Produits minces en alliages de titane bêta ou quasi bêta, fabrication par forgeage |
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 |
CN114178453A (zh) * | 2021-11-04 | 2022-03-15 | 大冶特殊钢有限公司 | 一种高合金方坯的径向锻造方法 |
CN114178453B (zh) * | 2021-11-04 | 2023-08-18 | 大冶特殊钢有限公司 | 一种高合金方坯的径向锻造方法 |
Also Published As
Publication number | Publication date |
---|---|
US20110192509A1 (en) | 2011-08-11 |
CA2737412A1 (fr) | 2010-03-25 |
RU2011115813A (ru) | 2012-10-27 |
CN102159340A (zh) | 2011-08-17 |
FR2936172B1 (fr) | 2012-07-06 |
CN102159340B (zh) | 2014-08-27 |
BRPI0919264A2 (pt) | 2015-12-15 |
EP2344290A1 (fr) | 2011-07-20 |
RU2510680C2 (ru) | 2014-04-10 |
EP2344290B1 (fr) | 2021-07-21 |
JP2012502803A (ja) | 2012-02-02 |
FR2936172A1 (fr) | 2010-03-26 |
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