EP2344290B1 - 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 PDF

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Publication number
EP2344290B1
EP2344290B1 EP09748827.4A EP09748827A EP2344290B1 EP 2344290 B1 EP2344290 B1 EP 2344290B1 EP 09748827 A EP09748827 A EP 09748827A EP 2344290 B1 EP2344290 B1 EP 2344290B1
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EP
European Patent Office
Prior art keywords
forging
blank
beta
billet
titanium alloy
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Application number
EP09748827.4A
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German (de)
English (en)
French (fr)
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EP2344290A1 (fr
Inventor
Xavier Baudequin
Gilbert Leconte
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP2344290A1 publication Critical patent/EP2344290A1/fr
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    • 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 process for forging a thermomechanical part made from a beta or alpha / beta titanium alloy.
  • the invention also relates to a method of manufacturing a thermomechanical part comprising this forging method.
  • thermomechanical part resulting from this forging process or from this manufacturing process, said thermomechanical part being a forged beta / alpha / beta alloy forging part having a fine and homogeneous microstructure with a grain size of l. of the order of 50 to 100 ⁇ m.
  • the invention also relates to a turbomachine comprising such a thermomechanical part.
  • EP 1 340 832 A1 discloses a process for forging beta or quasi-beta titanium alloys in which at least two forging steps are carried out comprising a first step in sub or super beta transus and a last step in super beta transus. During the forging process, the reduction rate at each step is greater than or equal to 2. This document takes account of a deformation on a macroscopic scale and not of a microscopic order.
  • the document JP 11077212 A1 discloses a method of forging a titanium ingot in which a first forging is performed at a low temperature in an alfa temperature range to give a first deformation to the ingot and then a second forging is performed in a beta temperature range, which is higher than the alfa range, and for each forging operation, the working ratio can take the values of 10%, 30% and 50%.
  • the invention defined in claims 1, 12 and 14, applies very particularly, but not restrictively, to the rotating parts of turbomachines, such as the discs, journals and impellers, and in particular to the discs of high pressure compressors, in particular to DAM (monobloc bladed discs). Such rotating parts typically have a thickness greater than 10 mm, or even 20 or 30 mm.
  • the present invention relates to all types of temperature-stabilized titanium alloy: titanium alloys of the beta and alpha / beta classes (we are talking here about the structure of the finished part).
  • the present invention relates very particularly to titanium alloys called “alpha / beta forged beta”, the designation “alpha / beta” corresponding to the microstructure of the part, namely with coexistence of the alpha and beta phases of titanium, this part being placed.
  • 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 T ⁇ , temperatures below the temperature of beta transus T ⁇ corresponding to the alpha / beta domain.
  • the forging process corresponds to the diagram of the figure 1 , described below.
  • a titanium alloy ingot obtained by fusion is transformed into a billet having any desired shape, which is mostly a cylindrical shape.
  • Such a billet constitutes a semi-finished 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 cross section of the ingot and obtain the billet with controlled metallurgical and dimensional characteristics.
  • the fusion (s ) are carried out according to one of the following techniques: remelting with a vacuum arc (“VAR” for “Vacuum Arc Remelting”) , remelting by electron beam in a cold crucible (“ EBCHR ”for“ Electron Beam Cold Heart Remelting ”) or by the technique of fusion by plasma beam (“ PAM ”for“ Plasma Arc Melting ”).
  • VAR vacuum arc
  • EBCHR Electron Beam Cold Heart Remelting
  • PAM plasma Arc Melting
  • This billet is then subjected to the forging process illustrated on figure 1 according to a plot of the temperature to which the billet 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 “blank forging”.
  • the billet is first heated (reference a) between times t 0 and t 1 from ambient temperature T 0 to temperature T 1 below the beta transus temperature T ⁇ .
  • this temperature T 1 is of the order of the beta transus temperature T ⁇ - 60 ° C and this rise in temperature, depending on the massiveness of the billet, takes, for example, about 2 hours for a billet of a diameter of 200 mm.
  • the billet is maintained at the temperature T 1 (mark b) between the times t 1 and t 2 , corresponding to a duration of about 1 hour or more, to ensure that all of the material constituting the billet has reached this temperature T 1 , before proceeding with the forging operation proper (reference c), that is to say the hot plastic deformation by press (stamping), pestle, rolling mill, etc. billet between the moments t 2 and t 3 , corresponding to a duration of a few tens of seconds, thus forming a blank.
  • the forging operation proper that is to say the hot plastic deformation by press (stamping), pestle, rolling mill, etc. billet between the moments t 2 and t 3 , corresponding to a duration of a few tens of seconds, thus forming a blank.
  • the blank being in the open air, it follows a natural cooling of a few tens of ° C of the surface of the part, while the core of the part either cools a little or heats up by a few ° C depending on the massiveness of the part and the forging conditions, in particular the rate of deformation.
  • the blank is allowed to cool (reference d) to ambient temperature T 0 , between times t 3 and t 4 , corresponding to a duration of approximately a few tens of minutes.
  • an alternative consists in starting a second rough forging earlier by heating (item e) the roughing between times t 3 and t 4 of the first rough forging, i.e. not to wait for complete cooling. up to ambient temperature T 0 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) up to temperature T 1 then one continues with a temperature maintenance (reference b ') preceding the forging operation. proper (reference c ').
  • This alternative makes it possible to reduce the time for implementing the forging process without the risk of causing the microstructure of the billet to change during complete cooling and a subsequent rise in temperature (marks d and a ′).
  • the second stage of forging or final forging which begins at time t n , it takes up stages similar to those of rough forging except for the value of the temperature at which The blank is carried before the actual forging operation is carried out, since it is the temperature T 2 greater than the beta transus temperature T ⁇ .
  • this temperature T 2 is of the order of the beta transus temperature T ⁇ + 25 ° C.
  • the final forging comprises heating the blank (reference A) between times t n and t n + 1 from ambient temperature T 0 to temperature T 2 , then maintaining temperature T 2 (reference B) between times t n + 1 and t n + 2 , before proceeding with the actual forging operation (reference C) of the blank between times t n + 2 and t n + 3 .
  • This forging operation (reference C) of the blank is carried out at temperature T 2 , in the beta range (temperature greater than T ⁇ ), the gradual cooling of the blank during this forging operation possibly leading to 'a part of the blank subjected to the forging operation has a temperature below T ⁇ and is therefore also forged at a temperature corresponding to the alpha / beta domain.
  • the forging part thus obtained is cooled (reference D), referred to as a forging blank or forged part, to the ambient temperature T 0 between the times t n + 3 and t n + 4 .
  • the other forging parameters of the rough forging and final forging stages including forging speed, transfer time between heating furnace and forging equipment, transfer time between forging equipment and system cooling of the part 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 rough forging as well as the characteristics of each forging operation proper (marks c, c ', ... C) of the rough forging and final forging stages in particular the choice of forging equipment (hydraulic press , mechanical screw press, ram, rolling mill), the position of the billet / blank in relation 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 part, according to its geometry and massiveness, according to a pre-established procedure making it possible to progressively deform the billet then the blank by forming, at the end of the process forging, a forged part having the required geometric characteristics.
  • the titanium alloy billet subjected to the forging manufacturing process described above initially has heterogeneous microstructures.
  • the case may be encountered of a microstructure containing one or more large grains of titanium, which may have a dimension of up to several millimeters, or even of the order of a centimeter, in particular of titanium in the 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 recrystallized grains of smaller size by the forging process described above.
  • the object of the present invention is to provide a forging process making it possible to overcome the drawbacks of the prior art and in particular offering the possibility of eliminating in the blank any presence of heterogeneous microstructures and in particular of a possible presence of coarse grains in the starting billet, in order to provide a homogeneous microstructure of the forged part.
  • the method is characterized in that said forging operation of the blank forging step produces at any point of said billet a local deformation greater than a minimum deformation rate of at least 0.2.
  • deformation rate is meant here the plastic deformation cumulated at a point of the part, also called equivalent deformation, which is therefore considered on the part having undergone the rough forging operation considered.
  • 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 forging operation proper (mark c and / or c ') of at least one of the forging operation.
  • rough forging steps that is to say for the forging operation (s) carried out in the alpha / beta domain, namely below the beta transus temperature T ⁇ .
  • the solution according to the invention on the one hand is applied 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 observed that the final forging step does not allow, and this regardless of the rate of deformation local affected, to produce fine and homogeneous microstructures, in particular if the blank (or the billet) first has a heterogeneous microstructure, in particular a microstructure with isolated coarse grains.
  • This solution also has the additional advantage of making it possible, moreover, to avoid a modification of the conditions for carrying out the final forging step which, due to the temperature reached (temperature T 2 > beta transus temperature T ⁇ ), is relatively difficult to implement.
  • a minimum deformation rate is provided, due to the forging operation proper of the blank forging step, of at least 0.2, preferably said minimum deformation rate is 0.3 and preferably 0.4.
  • the process relates to an alpha-beta type titanium alloy.
  • thermomechanical part obtained is a forged alpha / beta alloy forged beta part which has a finer or more refined microstructure compared 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.

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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)
EP09748827.4A 2008-09-22 2009-09-22 Procede de forgeage d'une piece thermomecanique en alliage de titane. Active EP2344290B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0856337A FR2936172B1 (fr) 2008-09-22 2008-09-22 Procede de forgeage d'une piece thermomecanique en alliage de titane
PCT/FR2009/051780 WO2010031982A1 (fr) 2008-09-22 2009-09-22 Procede de forgeage d'une piece thermomecanique en alliage de titane.

Publications (2)

Publication Number Publication Date
EP2344290A1 EP2344290A1 (fr) 2011-07-20
EP2344290B1 true EP2344290B1 (fr) 2021-07-21

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EP09748827.4A Active EP2344290B1 (fr) 2008-09-22 2009-09-22 Procede de forgeage d'une piece thermomecanique en alliage de titane.

Country Status (9)

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US (1) US20110192509A1 (zh)
EP (1) EP2344290B1 (zh)
JP (1) JP2012502803A (zh)
CN (1) CN102159340B (zh)
BR (1) BRPI0919264A2 (zh)
CA (1) CA2737412A1 (zh)
FR (1) FR2936172B1 (zh)
RU (1) RU2510680C2 (zh)
WO (1) WO2010031982A1 (zh)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2979702B1 (fr) 2011-09-05 2013-09-20 Snecma Procede de preparation d'eprouvettes de caracterisation mecanique d'un alliage de titane
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
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
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
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
CN113976658B (zh) * 2021-10-22 2024-06-25 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
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

Citations (1)

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Publication number Priority date Publication date Assignee Title
JPH1177212A (ja) * 1997-08-28 1999-03-23 Sumitomo Metal Ind Ltd チタンスラブの製造方法

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JPS57202935A (en) * 1981-06-04 1982-12-13 Sumitomo Metal Ind Ltd Forging method for titanium alloy
JPS58145323A (ja) * 1982-02-22 1983-08-30 Toshiba Corp チタン合金の鍛造方法
JPH0289532A (ja) * 1988-09-27 1990-03-29 Sumitomo Metal Ind Ltd チタン合金の恒温鍛造方法
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
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FR2836640B1 (fr) * 2002-03-01 2004-09-10 Snecma Moteurs Produits minces en alliages de titane beta ou quasi beta fabrication par forgeage
US6884279B2 (en) * 2002-07-25 2005-04-26 General Electric Company Producing metallic articles by reduction of nonmetallic precursor compounds and melting
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Also Published As

Publication number Publication date
FR2936172A1 (fr) 2010-03-26
CN102159340B (zh) 2014-08-27
RU2510680C2 (ru) 2014-04-10
JP2012502803A (ja) 2012-02-02
FR2936172B1 (fr) 2012-07-06
CN102159340A (zh) 2011-08-17
RU2011115813A (ru) 2012-10-27
US20110192509A1 (en) 2011-08-11
EP2344290A1 (fr) 2011-07-20
BRPI0919264A2 (pt) 2015-12-15
CA2737412A1 (fr) 2010-03-25
WO2010031982A1 (fr) 2010-03-25

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