US20090308506A1 - Methods for heat treating and manufacturing a thermomechanical part made of a titanium alloy, and thermomechanical part resulting from these methods - Google Patents
Methods for heat treating and manufacturing a thermomechanical part made of a titanium alloy, and thermomechanical part resulting from these methods Download PDFInfo
- Publication number
- US20090308506A1 US20090308506A1 US12/295,093 US29509307A US2009308506A1 US 20090308506 A1 US20090308506 A1 US 20090308506A1 US 29509307 A US29509307 A US 29509307A US 2009308506 A1 US2009308506 A1 US 2009308506A1
- Authority
- US
- United States
- Prior art keywords
- heat treatment
- thermomechanical
- temperature
- titanium alloy
- thermomechanical part
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims abstract description 53
- 230000000930 thermomechanical effect Effects 0.000 title claims abstract description 20
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 title claims description 9
- 238000000137 annealing Methods 0.000 claims abstract description 26
- 238000010438 heat treatment Methods 0.000 claims description 37
- 238000010791 quenching Methods 0.000 claims description 18
- 230000000171 quenching effect Effects 0.000 claims description 17
- 238000001816 cooling Methods 0.000 claims description 11
- 238000005496 tempering Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 description 15
- 239000000463 material Substances 0.000 description 14
- 229910045601 alloy Inorganic materials 0.000 description 11
- 239000000956 alloy Substances 0.000 description 11
- 238000012360 testing method Methods 0.000 description 10
- 230000007704 transition Effects 0.000 description 4
- 125000004122 cyclic group Chemical group 0.000 description 3
- 230000007547 defect Effects 0.000 description 3
- 238000005242 forging Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229920002959 polymer blend Polymers 0.000 description 2
- 230000002028 premature Effects 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000035508 accumulation Effects 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000003467 diminishing effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000035784 germination Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 230000002250 progressing effect Effects 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Images
Classifications
-
- 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 heat treating a thermomechanical part made of a TA6Zr4DE titanium alloy, to a fabrication method including such a heat treatment method, and to a thermomechanical part that results from those methods.
- the invention relates more particularly, but not exclusively, to rotary parts for turbomachines, such as disks, trunions, and impellers, and in particular to high pressure compressor disks.
- high pressure compressor disks are obtained by stamping the titanium alloy in the beta domain.
- an alloy such as “6242” that includes about 6% aluminum, 2% tin, 4% zirconium, and 2% molybdenum. More precisely, the alloy concerned is known as TA6Zr4DE in metallurgical nomenclature. The stamping is performed at about 1030° C.
- the stamping step is followed by a heat treatment method comprising a step of solution annealing in the alpha/beta domain of the alloy at a temperature of 970° C. for one hour, where 970° C. is 30° C. lower than to the beta transus temperature, i.e. corresponds to the beta transus temperature ⁇ 30° C.
- This solution-annealing step is followed by a step of quenching in oil or in a water-polymer mixture. Thereafter, tempering treatment is performed at 595° C. for eight hours, and finally cooling is performed in air.
- an alloy When implementing that heat treatment method, an alloy is obtained that presents a coarse microstructure that is not favorable to obtaining good strength for the titanium alloy, in particular when subjected to a creep test under an imposed stress that is maintained for a certain holding time, in particular for a range of utilization temperatures of ⁇ 50° C. to +25° C. It is the “dwell effect”, i.e. creep at fairly low temperature (lower than 200° C.), that leads to damage which, in association with oligocyclic fatigue, leads to premature failure of the part.
- An object of the present invention is to provide a method of heat treating a thermomechanical part made of a titanium alloy, which method can be implemented industrially and serves to overcome the drawbacks of the prior art, and in particular makes it possible to limit the extent of the “dwell effect” phenomenon.
- the heat treatment method is characterized in that a solution-annealing step is performed at a temperature lying in the range beta transus ⁇ 20° C. and beta transus ⁇ 15° C. for a duration lying in the range four hours to eight hours.
- This temperature condition corresponds to a maximum temperature of about 985° C.
- This difference relative to the beta transus temperature constitutes a safety margin, associated with the possibility of a difference between the temperature as measured and the real temperature of the alloy, and it serves to guarantee that the alloy remains below its beta transition temperature.
- This solution-annealing step is performed for four to eight hours depending on the size of the part.
- the idea on which the present invention is based corresponds to the fact that it has been observed that within the material there are to be found zones or colonies that are propitious for the “dwell effect” phenomenon. It is observed that such colonies are formed by elongate needle-type alpha phase grains that are relatively fat and that touch one another. In general, such grains present a length of several millimeters and a width of the order of 200 micrometers ( ⁇ m) to 300 mm. When stresses accumulate, such colonies constitute locations in which a large number of dislocations become concentrated such that, on becoming active, and without any particular thermal effect, they can cause slip to take place between the grains, which can lead to breakage.
- the present invention proposes implementing heat treatment that enables the microstructure to be refined, in particular by refining the size of the above-mentioned needle, so as to minimize the effects of the “dwell effect”, and in particular by diminishing the extent to which dislocations can move freely so as to minimize the extent to which they accumulate, thereby minimizing any risk of the part breaking.
- the solution-annealing step is performed for a duration that is much longer than is usual.
- the part is allowed to come close to or even to reach its microstructural equilibrium, thereby enabling the needles in the colonies that might give rise to the “dwell effect” to be reduced in size both in length and in thickness.
- This treatment enables a microstructure to be obtained that is finer than that in the prior art, and thus serves to minimize the consequences of the “dwell effect”.
- the present invention proposes performing this solution-annealing step at a temperature that is quite close to the beta transition temperature, while remaining strictly below said temperature, in order to obtain a microstructure for the final part that lies in the alpha/beta, near-alpha, and alpha classes.
- thermomechanical parts in particular high pressure compressor disks, presenting firstly lifetimes that are longer than those of parts obtained using previous techniques, but also presenting thermomechanical characteristics (strength in traction, in creep, in fatigue under imposed stress with holding time . . . ) that are at least as good, and while minimizing the risks of fatigue failure.
- the heat treatment method of the invention makes it possible to improve the ability to withstand the “dwell effect” by a factor of about two compared with a prior art heat treatment method, as shown by testing described below, where the “dwell effect” involves cyclical loading, with the loading being held for a certain length of time on each cycle to encourage creep.
- the method in accordance with the invention further includes a step whereby the part is quenched at a cooling rate greater than 200° C./min, and preferably lying in the range 300° C./min to 450° C./min.
- this cooling rate is as high as possible and is preferably greater than or of the order of 400° C./min.
- the state of the microstructure is frozen in the situation in which it is to be found at the end of the long solution-annealing step, thereby avoiding any new variation in this microstructure leading to growth of the needles in the alpha phase colonies, which growth would be propitious to the “dwell effect” phenomenon.
- this choice of a high quenching speed serves to encourage a martensitic type transformation of the beta phase into the alpha phase (and giving rise to a fairly fine microstructure), as compared with the germination/growth type phenomenon (which leads to a microstructure that is rather coarse).
- the method further includes the following steps:
- the invention also provides a method of fabricating a thermomechanical part made of a titanium alloy, by stamping in the beta domain, which fabrication method includes such a heat treatment method.
- the present invention also provides a thermomechanical part made of a titanium alloy in which the fabrication method includes the above-mentioned heat treatment method or results from the above-described fabrication method.
- the titanium thermomechanical part preferably forms a rotary part of a turbine engine, in particular a compressor disk, specifically for a high pressure compressor.
- the present invention also provides a turbomachine fitted with a thermomechanical part according to any of the definitions given above.
- FIG. 1 shows the microstructure obtained using the conventional heat treatment method of the prior art
- FIG. 2 shows the microstructure obtained using the conventional heat treatment method of the prior art as modified by a faster quenching speed
- FIG. 3 shows the microstructure obtained using the heat treatment method of the present invention
- FIG. 4 shows the microstructure obtained using the heat treatment method of the present invention with a faster quenching speed
- FIG. 5 shows the results of a creep test under cyclic loading with a load holding time for a part obtained by the prior art method and for a part obtained by the method in accordance with the invention.
- the present invention relates to all types of temperature-stabilized titanium alloy: titanium alloys in classes beta, alpha/beta, near-alpha, and alpha (with these terms relating to the structure of the finished part).
- the disks are obtained by forging using hot stamping in the beta domain of the titanium alloy.
- This stamping step is followed by a method of heat treatment comprising a step of solution annealing in the alpha/beta domain of the alloy at a temperature of 970° C., i.e. 30° C. lower than the beta transus temperature, and for one hour.
- This solution-annealing step is followed by a step of quenching in oil or in a water-polymer mixture (cooling rate of the order of 200° C./min and lying in the range 130° C./min to 250° C./min). Thereafter, a tempering operation is performed at 595° C. for eight hours, and finally cooling is performed in air.
- FIG. 1 That produces a material presenting the microstructure that can be seen in FIG. 1 , presenting colonies constituted by mutually parallel needles of beta phase. Those needles present a section of elongate shape that is visible in the figure, and often extending over several hundreds of micrometers.
- the microstructure that can be seen corresponds to that of a titanium alloy identical to the alloy of FIG. 1 , having been subjected to the above-described heat treatment with the exception of the following two differences:
- the colonies of parallel needles comprise needles that are more dissimilar in size, and in particular there are fewer large needles. Nevertheless, even though less numerous, it can be expected that there will be sufficient of these large needles for the “dwell effect” phenomenon to lead to accumulations of dislocations that are liable to give rise to risks of breakage.
- FIGS. 3 and 4 there can be seen the microstructures that are obtained by using the method in accordance with the present invention.
- the needles are all of smaller section size, of length that remains less than 100 ⁇ m, and is generally about 50 ⁇ m.
- the reduction in the size of the needles is accompanied by a reduction in their volume and in a reduction of the areas of joint between needles, thereby putting a brake on the ability to move of defects such as dislocations or vacancies, so they move over shorter distances and have less chance of accumulating.
- quenching was also performed at a faster rate, at 400° C./min instead of 200° C./min.
- the microstructures are frozen to a greater extent at a size that is smaller than the size of microstructures that give rise to damage in the material. This avoids needles or grains accumulating in the form of bunches of large-sized parallel needles that, like a single grain, concentrate defects at the edges of their interfaces.
- a test was performed under cyclic loading including a load holding time by implementing a cycle of trapezoid shape: increasing load for 1 second (s), load maintained constant for 120 s at 868 megapascals (MPa), followed by load dropping down to zero over 1 s.
- FIG. 5 is a graph showing the ratio of deformation over lengthening under cyclic loading with a load holding time, plotted as a function of the number of cycles to breakage.
- Curve A shows the result of that test for materials obtained using the heat treatment method of the prior art and having the microstructure of FIG. 1 .
- Curve B shows the result of that test for materials obtained using the heat treatment method of the present invention and having the microstructure of FIG. 4 .
- That standardized test thus shows that the heat treatment method of the present invention makes it possible practically to double the number of cycles before breaking, since the number is raised from 5500 cycles to 10,000 cycles.
- the present invention makes it possible, in particular by lengthening the duration of the solution-annealing step, significantly to improve lifetime during a fatigue strength test that includes a load-holding time.
- solution-annealing times are selected (e.g. eight hours), and for finer parts where it is possible to reach a quenching speed of 400° C./min, shorter solution-annealing times can be applied (e.g. four hours).
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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)
Applications Claiming Priority (3)
| 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 |
| FR0651111 | 2006-03-30 | ||
| 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 (1)
| Publication Number | Publication Date |
|---|---|
| US20090308506A1 true US20090308506A1 (en) | 2009-12-17 |
Family
ID=37517151
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US12/295,093 Abandoned US20090308506A1 (en) | 2006-03-30 | 2007-03-30 | Methods for heat treating and manufacturing a thermomechanical part made of a titanium alloy, and thermomechanical part resulting from these methods |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090308506A1 (fr) |
| EP (1) | EP2002026B1 (fr) |
| JP (1) | JP5525257B2 (fr) |
| FR (1) | FR2899241B1 (fr) |
| WO (1) | WO2007113445A2 (fr) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102758160A (zh) * | 2012-08-02 | 2012-10-31 | 西北工业大学 | 一种在近α钛合金中获得三态组织的方法 |
| CN102758158A (zh) * | 2012-08-02 | 2012-10-31 | 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 |
| CN102758161A (zh) * | 2012-08-02 | 2012-10-31 | 西北工业大学 | 一种在钛合金中获得三态组织的方法 |
| CN114606455A (zh) * | 2022-05-11 | 2022-06-10 | 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 |
| US11725516B2 (en) * | 2019-10-18 | 2023-08-15 | Raytheon Technologies Corporation | Method of servicing a gas turbine engine or components |
Families Citing this family (3)
| 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 |
Citations (6)
| 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 |
| US4842652A (en) * | 1987-11-19 | 1989-06-27 | United Technologies Corporation | Method for improving fracture toughness of high strength titanium alloy |
| 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 |
| US20050284549A1 (en) * | 2004-06-28 | 2005-12-29 | General Electric Company | Method for producing a beta-processed alpha-beta titanium-alloy article |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
-
2006
- 2006-03-30 FR FR0651111A patent/FR2899241B1/fr active Active
-
2007
- 2007-03-30 JP JP2009502173A patent/JP5525257B2/ja active Active
- 2007-03-30 WO PCT/FR2007/051046 patent/WO2007113445A2/fr active Application Filing
- 2007-03-30 US US12/295,093 patent/US20090308506A1/en not_active Abandoned
- 2007-03-30 EP EP07731850A patent/EP2002026B1/fr active Active
Patent Citations (7)
| 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 |
| US4842652A (en) * | 1987-11-19 | 1989-06-27 | United Technologies Corporation | Method for improving fracture toughness of high strength titanium alloy |
| 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 |
| US5849112A (en) * | 1994-11-15 | 1998-12-15 | Boeing North American, Inc. | Three phase α-β titanium alloy microstructure |
| US6284070B1 (en) * | 1999-08-27 | 2001-09-04 | General Electric Company | Heat treatment for improved properties of alpha-beta titanium-base alloys |
| US20050284549A1 (en) * | 2004-06-28 | 2005-12-29 | General Electric Company | Method for producing a beta-processed alpha-beta titanium-alloy article |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102758160A (zh) * | 2012-08-02 | 2012-10-31 | 西北工业大学 | 一种在近α钛合金中获得三态组织的方法 |
| CN102758158A (zh) * | 2012-08-02 | 2012-10-31 | 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 |
| CN102758161A (zh) * | 2012-08-02 | 2012-10-31 | 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 |
| CN114606455A (zh) * | 2022-05-11 | 2022-06-10 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2007113445A2 (fr) | 2007-10-11 |
| WO2007113445A3 (fr) | 2007-12-13 |
| JP2009531546A (ja) | 2009-09-03 |
| FR2899241B1 (fr) | 2008-12-05 |
| FR2899241A1 (fr) | 2007-10-05 |
| EP2002026B1 (fr) | 2011-09-14 |
| EP2002026A2 (fr) | 2008-12-17 |
| JP5525257B2 (ja) | 2014-06-18 |
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| Date | Code | Title | Description |
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| AS | Assignment |
Owner name: SNECMA, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BARBIER, BLANDINE;GALLOIS, PHILIPPE;MONS, CLAUDE MARCEL;AND OTHERS;REEL/FRAME:022483/0703 Effective date: 20090227 |
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