EP2002026B1 - Procedes de traitement thermique et de fabrication d'une piece thermomecanique realisee dans un alliage de titane - Google Patents

Procedes de traitement thermique et de fabrication d'une piece thermomecanique realisee dans un alliage de titane Download PDF

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Publication number
EP2002026B1
EP2002026B1 EP07731850A EP07731850A EP2002026B1 EP 2002026 B1 EP2002026 B1 EP 2002026B1 EP 07731850 A EP07731850 A EP 07731850A EP 07731850 A EP07731850 A EP 07731850A EP 2002026 B1 EP2002026 B1 EP 2002026B1
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EP
European Patent Office
Prior art keywords
temperature
heat treatment
beta
titanium alloy
transus
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EP07731850A
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German (de)
English (en)
French (fr)
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EP2002026A2 (fr
Inventor
Blandine Barbier
Philippe Gallois
Claude Mons
Alain Perroux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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 thermal treatment method of a thermomechanical part made of a titanium alloy TA6Zr4DE, and a manufacturing method comprising such a heat treatment process.
  • the invention is particularly, but not exclusively, applicable to rotating parts of turbomachines, such as discs, journals and wheels, and in particular to high-pressure compressor discs.
  • the high pressure compressor discs are obtained by stamping in the beta domain of the titanium alloy.
  • an alloy called “6242” which comprises about 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum. It is more specifically the TA6Zr4DE alloy according to the metallurgical nomenclature. This stamping is performed at about 1030 ° C.
  • This mastering step is followed by a heat treatment process comprising a solution step in the alpha / beta domain of the alloy at a temperature of 970 ° C., corresponding to the beta-30 ° C transus temperature, during one hour.
  • This dissolution step is followed by an oil quenching step or in a water-polymer mixture. Then, a treatment of income is carried out at 595 ° C for eight hours and finally air cooling is carried out.
  • this heat treatment process leads to an alloy having a coarse microstructure which is not conducive to good strength of the titanium alloy, in particular according to a stress creep test imposed for a certain holding time, especially for a range of operating temperature between -50 ° C and +250 ° C.
  • the application in the aeronautical field, and in particular for a high pressure compressor disk is very conducive to this phenomenon of "dwell effect" because during the take-off and landing phases, the engines are subject to operating conditions in the temperature and stress range corresponding to this phenomenon. This phenomenon can lead to ignition premature fatigue cracks, or even the rupture of the room.
  • the object of the present invention is to provide a heat treatment method for a thermomechanical part made of a titanium alloy which can be used industrially and makes it possible to overcome the drawbacks of the prior art and in particular to offer the possibility of to limit the extent of the "dwell effect" phenomenon.
  • the heat treatment process is characterized in that a dissolution step is carried out at a temperature of between ⁇ transus - 20 ° C and ⁇ transus - 15 ° C for a duration of 4 to 8 hours; and in that after the solution step a step of quenching the workpiece at a cooling rate of greater than 200 ° C / min is performed.
  • This temperature condition corresponds to a maximum temperature of about 985 ° C.
  • This difference with respect to the ⁇ -transus temperature is a safety margin, which is linked to the possible difference between the measured temperature and the actual temperature of the alloy, making it possible to ensure that the temperature remains below the temperature beta transition.
  • This dissolution step is performed for 4 to 8 hours depending on the size of the room.
  • the idea underlying the present invention corresponds to the fact that it has been found that there exist within the material zones or colonies, conducive to the phenomenon of "dwell effect". It is found that such colonies are formed of elongated grains of alpha phase, needle-like, relatively big and joined together. Generally, such grains have a length of several millimeters over a width of the order of 200 to 300 microns. Such colonies constitute locations at which, when stresses are accumulated, a large concentration of dislocations occurs which, when activated, without any particular thermal effect, can cause slips between the grains, which can lead to to breaks.
  • the present invention proposes to implement a heat treatment making it possible to refine the microstructure, in particular the size of the aforementioned needles, in order to minimize the effects of the "dwell effect", and this by reducing the extent of free circulation of the dislocations , to minimize their accumulation and, in this way, the risk of breakage of the room.
  • the solution-making step is carried out for a much longer period than that usually performed.
  • the piece is allowed to come closer, even to reach, its microstructural equilibrium, which makes it possible to reduce the size, in length and thickness, of the needles of the colonies likely to cause the "dwell effect” .
  • This treatment makes it possible to obtain a finer microstructure than that of the prior art, and thus to minimize the consequences of the "dwell effect".
  • thermomechanical properties of the material does not have the consequence, contrary to the prevailing prejudices in this field of metallurgy, to affect the thermomechanical properties of the material.
  • the inventors have, in the context of the invention presented here, implemented a heat treatment process whose solution solution stage was carried out for a much longer duration than that practiced usually, without the material resulting from the entire heat treatment process having thermomechanical characteristics, and in particular imposed fatigue fatigue properties, lower than those of the materials resulting from the treatment process thermal of the prior art.
  • the present invention proposes to carry out this dissolution step at a temperature relatively close to the beta transition temperature, while remaining strictly lower than the latter, and this in order to obtain a microstructure of the final piece in the classes of alpha / beta, almost alpha and alpha.
  • thermomechanical parts in particular discs for high pressure compressor, having on the one hand durability greater than that of the parts obtained according to the techniques previously used, but also having thermomechanical characteristics (traction, creep, stress fatigue imposed during a holding time ...) at least as good, while minimizing the risks of fatigue rupture.
  • the thermal treatment method according to the invention allows a gain of a factor of about two on the resistance to "dwell" (cyclic loading with hold-load time - creep - at each cycle) compared to a method of treatment, as shown in the tests described below.
  • a step of quenching the workpiece at a cooling rate of greater than 200 ° C./min and preferably of between 300 and 450 ° C. is carried out after the dissolving step.
  • this cooling rate is the largest possible and preferably greater than or of the order of 400 ° C / min.
  • the present invention also relates to a method of manufacturing a thermomechanical part made of a titanium alloy, by stamping in the ⁇ domain, comprising such a heat treatment process.
  • the present invention relates to all types of titanium alloy stabilized in temperature: titanium alloys of the beta, alpha / beta, almost alpha and alpha (this is called the structure of the finished part).
  • This mastering step is followed by a heat treatment process comprising a solution step in the alpha / beta domain of the alloy at a temperature of 970 ° C., corresponding to the beta-30 ° C transus temperature, during one hour.
  • This dissolution step is followed by an oil quenching step or in a water-polymer mixture (cooling rate of the order of 200 ° C./min and between 130 and 250 ° C./min). .
  • a treatment of income is carried out at 595 ° C for eight hours and finally air cooling is carried out.
  • a material having the microstructure visible on the figure 1 having colonies consisting of beta phase needles parallel to each other. These needles have an elongate section visible in the figure often extending over several hundred micrometers.
  • parallel needle colonies have needles more dissimilar in size and in particular there are fewer large needles. Nevertheless, even in fewer numbers, it is expected that these large needles are sufficient in number for the phenomenon of "dwell effect" causes accumulations of dislocations likely to cause risks of rupture.
  • the needles are all smaller in section, their length remaining less than 100 micrometers, and generally of the order of 50 micrometers.
  • the decrease in the size of the needles is accompanied by a decrease in their volume and the contiguous surfaces between needles, which hampers the ability to move defects such as dislocations or gaps, which run thus smaller distances and less opportunities to accumulate.
  • the microstructures are more freeze to a smaller size than those which generate the damages of the material. This avoids the accumulation of needles or grains, in the form of large parallel needle packets which, like a single grain, concentrate defects at the edge of their interface.
  • a cyclic loading test was carried out with hold-up time, of the trapezoidal cycle type: load increase during 1s, maintenance hold of 120s at 868 MPa, then descent at zero load for 1s .
  • Curve A represents the result of this test for materials obtained according to the heat treatment process of the prior art and in accordance with the microstructure of the figure 1
  • Curve B represents the result of this test for materials obtained according to the heat treatment process of the present invention and conform to the microstructure of the figure 4 .
  • the present invention makes it possible, surprisingly, in particular by extending the duration of the solution-making step, to significantly improve the fatigue test life with hold time. This is mainly due to the fact that this elongation makes it possible to refine the microstructure and in particular to reduce the size of the alpha phase needles forming the colonies that are sensitive to the "dwell effect" phenomenon.
  • the increase of the dissolution temperature favors the solution of the coarse primary alpha phase in order to transform it into a beta phase.
  • the transus beta temperature of the alloy since it is fundamental not to exceed the transus beta temperature of the alloy, we will choose a temperature that does not exceed the temperature transus beta -15 ° C.
  • This upper limit of the dissolution temperature is chosen according to the precision of the knowledge of the transus beta temperature and the class of the treatment furnaces.
  • forging sub-transus that is to say above the beta transition temperature, one will of course choose a solution temperature higher than the forging temperature.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat Treatment Of Articles (AREA)
EP07731850A 2006-03-30 2007-03-30 Procedes de traitement thermique et de fabrication d'une piece thermomecanique realisee dans un alliage de titane Active EP2002026B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0651111A FR2899241B1 (fr) 2006-03-30 2006-03-30 Procedes de traitement thermiques et de fabrication d'une piece thermomecanique realisee dans un alliage de titane, et piece thermomecanique resultant de ces procedes
PCT/FR2007/051046 WO2007113445A2 (fr) 2006-03-30 2007-03-30 Procedes de traitement thermique et de fabrication d'une piece thermomecanique realisee dans un alliage de titane, et piece thermomecanique resultant de ces procedes

Publications (2)

Publication Number Publication Date
EP2002026A2 EP2002026A2 (fr) 2008-12-17
EP2002026B1 true EP2002026B1 (fr) 2011-09-14

Family

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EP07731850A Active EP2002026B1 (fr) 2006-03-30 2007-03-30 Procedes de traitement thermique et de fabrication d'une piece thermomecanique realisee dans un alliage de titane

Country Status (5)

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US (1) US20090308506A1 (ja)
EP (1) EP2002026B1 (ja)
JP (1) JP5525257B2 (ja)
FR (1) FR2899241B1 (ja)
WO (1) WO2007113445A2 (ja)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2952559B1 (fr) * 2009-11-16 2011-12-09 Snecma Procede de fabrication d'alliages de titane avec forgeages a temperatures incrementees
FR2979702B1 (fr) 2011-09-05 2013-09-20 Snecma Procede de preparation d'eprouvettes de caracterisation mecanique d'un alliage de titane
FR2982279B1 (fr) * 2011-11-08 2013-12-13 Snecma Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de
CN102758160B (zh) * 2012-08-02 2013-10-09 西北工业大学 一种在近α钛合金中获得三态组织的方法
CN102758158B (zh) * 2012-08-02 2013-12-04 西北工业大学 一种近α钛合金在α+β两相区获得三态组织的方法
CN102758161B (zh) * 2012-08-02 2013-12-25 西北工业大学 一种在钛合金中获得三态组织的方法
US11725516B2 (en) * 2019-10-18 2023-08-15 Raytheon Technologies Corporation Method of servicing a gas turbine engine or components
CN114606455B (zh) * 2022-05-11 2022-07-15 北京煜鼎增材制造研究院有限公司 大型钛合金构件喷淋式热处理方法

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3901743A (en) * 1971-11-22 1975-08-26 United Aircraft Corp Processing for the high strength alpha-beta titanium alloys
US4309226A (en) * 1978-10-10 1982-01-05 Chen Charlie C Process for preparation of near-alpha titanium alloys
JPS62205253A (ja) * 1986-03-05 1987-09-09 Kobe Steel Ltd Ｔｉ−８Ａｌ−１Ｍｏ−１Ｖ合金の熱処理方法
FR2614040B1 (fr) * 1987-04-16 1989-06-30 Cezus Co Europ Zirconium Procede de fabrication d'une piece en alliage de titane et piece obtenue
JPH01127653A (ja) * 1987-11-12 1989-05-19 Sumitomo Metal Ind Ltd α＋β型チタン合金冷延板の製造方法
US4842652A (en) * 1987-11-19 1989-06-27 United Technologies Corporation Method for improving fracture toughness of high strength titanium alloy
DE3804358A1 (de) * 1988-02-12 1989-08-24 Ver Schmiedewerke Gmbh Optimierung der waermebehandlung zur erhoehung der kriechfestigkeit warmfester titanlegierungen
JPH0621305B2 (ja) * 1988-03-23 1994-03-23 日本鋼管株式会社 耐熱チタン合金
JPH0222435A (ja) * 1988-07-11 1990-01-25 Nkk Corp 耐熱チタン合金
US5026520A (en) * 1989-10-23 1991-06-25 Cooper Industries, Inc. Fine grain titanium forgings and a method for their production
JP3314408B2 (ja) * 1992-04-24 2002-08-12 大同特殊鋼株式会社 チタン合金部材の製造方法
US5698050A (en) * 1994-11-15 1997-12-16 Rockwell International Corporation Method for processing-microstructure-property optimization of α-β beta titanium alloys to obtain simultaneous improvements in mechanical properties and fracture resistance
US6284070B1 (en) * 1999-08-27 2001-09-04 General Electric Company Heat treatment for improved properties of alpha-beta titanium-base alloys
US7449075B2 (en) * 2004-06-28 2008-11-11 General Electric Company Method for producing a beta-processed alpha-beta titanium-alloy article

Also Published As

Publication number Publication date
WO2007113445A3 (fr) 2007-12-13
FR2899241B1 (fr) 2008-12-05
JP2009531546A (ja) 2009-09-03
FR2899241A1 (fr) 2007-10-05
EP2002026A2 (fr) 2008-12-17
WO2007113445A2 (fr) 2007-10-11
JP5525257B2 (ja) 2014-06-18
US20090308506A1 (en) 2009-12-17

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