US20140286783A1 - Method of fabricating a part made out of ta6zr4de titanium alloy - Google Patents

Method of fabricating a part made out of ta6zr4de titanium alloy Download PDF

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Publication number
US20140286783A1
US20140286783A1 US14/353,404 US201214353404A US2014286783A1 US 20140286783 A1 US20140286783 A1 US 20140286783A1 US 201214353404 A US201214353404 A US 201214353404A US 2014286783 A1 US2014286783 A1 US 2014286783A1
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United States
Prior art keywords
heat treatment
cooling
fabrication method
stamping
die
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Abandoned
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US14/353,404
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English (en)
Inventor
Marion Derrien
Philippe Rochette
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ROCHETTE, Philippe, DERRIEN, Marion
Publication of US20140286783A1 publication Critical patent/US20140286783A1/en
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • 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
    • F05D2230/40—Heat treatment
    • 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
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the invention relates to a thermomechanical method of fabricating a part that is made of TA6Zr4DE titanium alloy, and to a part resulting from the method.
  • the invention applies particularly, but not exclusively, to rotary parts of turbomachines, such as disks, trunions, and impellers, and in particular it relates to high pressure compressor disks.
  • high pressure compressor disks are obtained by forging, comprising a step of forging a blank in the alpha/beta domain and a step of hot die-stamping in the beta domain of the titanium alloy.
  • the die-stamping is performed at about 1030° C.
  • This step of die-stamping in a press is followed by a heat treatment cycle comprising a step of solution treatment in the alpha/beta domain of the alloy at a temperature of 970° C., corresponding to the beta transus temperature minus 30° C., for one hour.
  • This solution treatment step is followed by a step of quenching in oil or in a water-polymer mixture.
  • annealing treatment is performed at 595° C. for eight hours followed by cooling in air.
  • an alloy is obtained that presents zones of coarse microstructure that are not favorable to good strength of the titanium alloy, in particular during oligo cycle fatigue testing with an imposed stress maintained for a certain dwell time in comparison with the same type of fatigue testing without a dwell time, in particular for a range of utilization temperatures extending from ⁇ 50° C. to +200° C.
  • the shortening in lifetime observed during such fatigue testing as a result of introducing a dwell time during which the maximum load is maintained leads to a phenomenon that is referred to as the dwell effect. More precisely, it comprises creep at a relatively low temperature (lower than 200° C.) which, coupled with oligo cycle fatigue, leads to internal damage in the material that may go as far as premature collapse of the part.
  • an alloy known as “6242” that includes about 6% aluminum, 2% tin, 4% zirconium, and 2% molybdenum. More precisely, this is known as the TA6Zr4DE alloy in metallurgical nomenclature.
  • FIG. 1 The type of structure that is conducive to the dwell effect phenomenon is shown in FIG. 1 : non-tangled needles all presenting a common orientation are located one either side of a grain boundary 10 .
  • this configuration which may be referred to as a “feather” structure, the needles are parallel to one another.
  • An object of the present invention is to provide a method of fabricating a thermomechanical part made of a TA6Zr4DE titanium alloy that can be performed industrially and that makes it possible to overcome the drawbacks of the prior art, and in particular that provides a possibility of limiting the extent of the dwell effect phenomenon.
  • An object of the present invention is to improve the thermomechanical fabrication method so as to obtain parts for which lifetime relating to the dwell effect phenomenon is increased, in spite of the cyclical stresses to which the parts are subjected at low temperature.
  • the present invention relates to a method of fabricating a thermomechanical part made of TA6Zr4DE titanium alloy, the method comprising a step of forging a blank in the alpha/beta domain to form a preform, a step of hot die-stamping the preform in order to form a rough part in the beta domain of the titanium alloy, and heat treatment, the method being characterized in that during the die-stamping step, the rough part is subjected throughout to local deformation s greater than or equal to 1.2, this die-stamping step terminating with immediate cooling at an initial cooling rate faster than 85 degrees Celsius per minute (C/min), and preferably faster than 100° C./min.
  • C/min degrees Celsius per minute
  • the present invention seeks to provide a fabrication method that makes it possible to limit grain size and to limit structures of the “colony” type, in particular by seeking to obtain a structure of the “tangled” type, so as to minimize the dwell effect, with this being done by reducing the extent over which dislocations can move freely, so as to minimize accumulation of dislocations and minimize the risk of the part breaking.
  • the cooling terminating the die-stamping is performed by quenching in water, in particular in water at a temperature that does not exceed 60° C.
  • said heat treatment includes solution heat treatment in the alpha/beta domain of the alloy immediately followed by cooling at a cooling rate faster than 100° C./min throughout the part.
  • the cooling terminating the solution heat treatment is performed by a step of quenching the part at a cooling rate faster than 150° C./min, and in particular a rate lying in the range 200° C./min to 450° C./min.
  • the cooling terminating the solution heat treatment is performed by quenching in oil or in a water/polymer mixture.
  • selecting a fast quench helps encourage a martensitic type transformation of the beta phase into an alpha phase (thereby leading to a microstructure that is rather fine), in comparison with the seeding/growth type phenomenon (which leads to a microstructure that is rather coarse).
  • the method further includes the following step:
  • the fabrication method of the invention also includes, between the die-stamping step (followed by cooling in water) and the solution heat treatment step, a step of machining, and in particular of pre-machining, seeking to diminish the massivity of the part. Other machining operations will follow to rectify the dimensions of the part and reach its final shape.
  • the present invention also provides a thermomechanical part made out of a TA6Zr4DE titanium alloy using the fabrication method as described above.
  • the present invention also relates to a turbomachine fitted with a thermomechanical part complying with any of the definitions given above.
  • FIG. 2 shows the microstructure of the type obtained with the fabrication method of the present invention
  • FIG. 3 shows the steps of the fabrication methods of the prior art and of the invention.
  • FIG. 4 shows the lifetime results of a fatigue test (“trapezoid” cycles with dwell time) at ambient temperature for a part obtained by the fabrication method of the prior art and for a part obtained by the fabrication method in accordance with the invention, with this being done over two zones of the part of different massivity (zones referenced 3 and 5 ).
  • a blank or billet of material is forged in the alpha/beta domain, e.g. at 950° C., followed by cooling in air in order to form a preform.
  • the preform is then subjected to a step of hot die-stamping in the beta domain of the titanium alloy at a temperature of 1030° C., corresponding to the beta transus temperature plus 30° C., followed by cooling in water after forging, thereby obtaining a rough part (also known as a “blank forging”) for forming a disk.
  • a step of hot die-stamping in the beta domain of the titanium alloy at a temperature of 1030° C., corresponding to the beta transus temperature plus 30° C., followed by cooling in water after forging, thereby obtaining a rough part (also known as a “blank forging”) for forming a disk.
  • This die-stamping step is followed by heat treatment comprising a solution heat treatment step in the alpha/beta domain of the alloy at a temperature of 970° C., corresponding to the beta transus temperature minus 30° C., for one hour.
  • This solution heat treatment step is followed by a step of quenching in oil or in a water-polymer mixture (minimum initial cooling rate of about 200° C. and then lying in the range 200° C./min to 450° C./min.
  • annealing heat treatment is performed at 595° C. for eight hours with cooling in air.
  • a material is obtained that presents the microstructure visible in FIG. 1 , presenting in certain locations colonies that are made up of mutually parallel alpha phase needles situated on either side of a grain boundary. These needles present a section of elongate shape that can be seen in the figure and they often extend over several hundreds of micrometers.
  • the visible microstructure corresponds to that of a titanium alloy identical to the alloy of FIG. 1 , and that has been subjected to the above-described fabrication method, with the exception of the following difference:
  • the needles are tangled and, furthermore, they are of different sizes. As can be seen in FIG. 2 , all of the needles are of smaller size in section, their length remaining less than 100 micrometers ( ⁇ m) and generally lying in the range about 20 ⁇ m to 50 ⁇ m.
  • the term local deformation ⁇ is used to mean the equivalent generalized deformation in the Von Mises sense as calculated by the Forge 2005 simulation software.
  • the equation used for calculation is as follows:
  • CAD computer-aided design
  • the material that results from the fabrication method as a whole presents thermomechanical characteristics, and in particular properties for withstanding oligo cycle fatigue under all imposed deformations, that are not any worse than those of the materials resulting from the prior art fabrication method.
  • a test of ability to withstand oligo cycle fatigue with imposed stress has been undertaken using a signal of trapezoidal shape (1 second (s) without stress, 40 s with stress, 1 s without stress) using a maximum stress of 772 megapascals (MPa) at ambient temperature for a high pressure compressor disk.
  • Zone 3 Mean Zone 5
  • Mean Standard 88278 91754 30003 28000 range- 95235 25997
  • lifetime is increased by a factor of 3 for a part obtained by the fabrication method of the invention compared with a part obtained from a standard range, in terms of a vibratory fatigue test with imposed stress at ambient temperature, at a frequency of 80 hertz (Hz).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Forging (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/353,404 2011-11-08 2012-11-08 Method of fabricating a part made out of ta6zr4de titanium alloy Abandoned US20140286783A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1160145A FR2982279B1 (fr) 2011-11-08 2011-11-08 Procede de fabrication d'une piece realisee dans un alliage de titane ta6zr4de
FR1160145 2011-11-08
PCT/FR2012/052581 WO2013068699A1 (fr) 2011-11-08 2012-11-08 PROCEDE DE FABRICATION D'UNE PIECE REALISEE DANS UN ALLIAGE DE TITANE TA6Zr4DE

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US20140286783A1 true US20140286783A1 (en) 2014-09-25

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US14/353,404 Abandoned US20140286783A1 (en) 2011-11-08 2012-11-08 Method of fabricating a part made out of ta6zr4de titanium alloy

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US (1) US20140286783A1 (ja)
EP (1) EP2776599B1 (ja)
JP (1) JP6189314B2 (ja)
CN (1) CN103906851B (ja)
BR (1) BR112014010218B1 (ja)
CA (1) CA2853183A1 (ja)
FR (1) FR2982279B1 (ja)
RU (1) RU2616691C2 (ja)
WO (1) WO2013068699A1 (ja)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210115794A1 (en) * 2019-10-18 2021-04-22 United Technologies Corporation Method of servicing a gas turbine engine or components
CN113118349A (zh) * 2019-12-30 2021-07-16 西北工业大学 一种Ti6242钛合金大厚度饼坯的制备方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201713483D0 (en) * 2017-08-22 2017-10-04 Imp Innovations Ltd A method for forming sheet material components

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4309226A (en) * 1978-10-10 1982-01-05 Chen Charlie C Process for preparation of near-alpha titanium alloys
JPS63130755A (ja) * 1986-11-21 1988-06-02 Sumitomo Metal Ind Ltd α＋β型チタン合金の加工熱処理方法
US6401537B1 (en) * 1999-07-02 2002-06-11 General Electric Company Titanium-based alloys having improved inspection characteristics for ultrasonic examination, and related processes
FR2836640B1 (fr) * 2002-03-01 2004-09-10 Snecma Moteurs Produits minces en alliages de titane beta ou quasi beta fabrication par forgeage
US7008491B2 (en) * 2002-11-12 2006-03-07 General Electric Company Method for fabricating an article of an alpha-beta titanium alloy by forging
FR2899241B1 (fr) * 2006-03-30 2008-12-05 Snecma Sa Procedes de traitement thermiques et de fabrication d'une piece thermomecanique realisee dans un alliage de titane, et piece thermomecanique resultant de ces procedes
FR2936173B1 (fr) * 2008-09-22 2012-09-21 Snecma Procede pour la fabrication d'une piece en titane avec forgeage initial dans le domaine beta
FR2936172B1 (fr) * 2008-09-22 2012-07-06 Snecma Procede de forgeage d'une piece thermomecanique en alliage de titane

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050284549A1 (en) * 2004-06-28 2005-12-29 General Electric Company Method for producing a beta-processed alpha-beta titanium-alloy article

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Von Mises Stress http://www.continuummechanics.org/vonmisesstress.html (2012) *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210115794A1 (en) * 2019-10-18 2021-04-22 United Technologies Corporation Method of servicing a gas turbine engine or components
US11725516B2 (en) * 2019-10-18 2023-08-15 Raytheon Technologies Corporation Method of servicing a gas turbine engine or components
CN113118349A (zh) * 2019-12-30 2021-07-16 西北工业大学 一种Ti6242钛合金大厚度饼坯的制备方法

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Publication number Publication date
CA2853183A1 (fr) 2013-05-16
JP6189314B2 (ja) 2017-08-30
WO2013068699A1 (fr) 2013-05-16
EP2776599B1 (fr) 2017-10-11
BR112014010218A8 (pt) 2017-06-20
BR112014010218A2 (pt) 2017-06-13
RU2616691C2 (ru) 2017-04-18
EP2776599A1 (fr) 2014-09-17
RU2014123323A (ru) 2015-12-20
CN103906851B (zh) 2016-10-26
CN103906851A (zh) 2014-07-02
BR112014010218B1 (pt) 2022-09-20
JP2015501878A (ja) 2015-01-19
FR2982279B1 (fr) 2013-12-13
FR2982279A1 (fr) 2013-05-10

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