EP0792945B1 - Procédé de traitement thermique d'un superalliage à base de nickel - Google Patents

Procédé de traitement thermique d'un superalliage à base de nickel Download PDF

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Publication number
EP0792945B1
EP0792945B1 EP19970400438 EP97400438A EP0792945B1 EP 0792945 B1 EP0792945 B1 EP 0792945B1 EP 19970400438 EP19970400438 EP 19970400438 EP 97400438 A EP97400438 A EP 97400438A EP 0792945 B1 EP0792945 B1 EP 0792945B1
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EP
European Patent Office
Prior art keywords
gamma
less
temperature
superalloy
prime solvus
Prior art date
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Expired - Lifetime
Application number
EP19970400438
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German (de)
English (en)
French (fr)
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EP0792945A1 (fr
Inventor
Yves Philippe Marc Desvallees
Jean-Michel Patrick Maurice Franchet
Michel Marty
Henri Octor
Françoise Passilly
Michèle Soucail
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Office National dEtudes et de Recherches Aerospatiales ONERA
Safran Aircraft Engines SAS
Original Assignee
Office National dEtudes et de Recherches Aerospatiales ONERA
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0792945A1 publication Critical patent/EP0792945A1/fr
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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
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Definitions

  • the present invention relates to a process for heat treatment of a nickel-based superalloy whose chemical composition in weight percentages is in accordance with either EP-B-0 237 378 and belongs to the following field: Cr 11 to 13; Co 8 to 17; Mo 6 to 8; Nb less than or equal to 1.5; Ti 4 to 5; Al 4 to 5; Hf less than or equal to 1; C, B, Zr each less than or equal to 500 ppm; No complement to 100, i.e.
  • FR 95.09653 which corresponds to EP-A-758 684 and FR-A-2 737 733 and belongs to the following field: Cr 12 to 15; Co 14.5 to 15.5; Mo 2 to 4.5; W o to 4.5; Al 2.5-4; Ti 4 to 6; Hf less than or equal to 0.5; C 100 to 300 ppm; B 100 to 500 PPm; Zr 200 to 700 ppm; No complement to 100.
  • alloys are used in particular for the manufacture of highly stressed parts intended for aircraft engines, for example rotor discs.
  • parts of this type can in particular be produced at using processing techniques from powders and their shaping calls for forging operations.
  • Heat treatments applied to the front parts job routinely include a layoff treatment in solution and quenching followed by a treatment of aging.
  • Documents US-A-5,547,523, US-A-5,529,643, EP-A-787,815 and EP-A-726,333 disclose superalloys subjected to intermediate heat treatments (between forging and supersolvus treatment).
  • the invention applies in particular in cases where is performed a supersolvus heat treatment comprising a complete solution of gamma-prime precipitates at one temperature between + 5 ° C and + 25 ° C above the gamma-prime solvus temperature for a period of maintenance between 1 hour and 4 hours.
  • the final grain size depends on a succession of stages that are: the possible pre-treatment of powders, densification by spinning, isothermal forging, the final heat treatment.
  • the parameters metallurgical and thermomechanical that can influence the recrystallization are numerous and interdependent. Let us quote: gamma-prime phase precipitation, distribution oxycarbon, the rate of deformation, the speed of deformation, stress, time, temperature.
  • the grain enlargement phenomenon caused by the heat treatment mentioned above can correspond to the following scheme: the gamma-prime precipitates which before the supersolvus heat treatment blocked the grain boundaries dissolve and the grain boundaries, released, migrate then are generally again anchored by very fine precipitates, oxycarbons, preferentially located at the old powder boundaries.
  • the result sought in this case is to obtain grains of uniform size, in particular of 50 ⁇ m on average, corresponding to a so-called normal grain growth.
  • thermomechanical cycle comprising at least one hot forging operation, carried out at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvus temperature minus 45 ° C , at a rational strain rate between 5.10 -5 s -1 and 2.10 -2 s -1 and at a rational strain rate greater than 0.1 and a supersolvus heat treatment, carried out at a temperature between the solvent temperature gamma-prime plus 5 ° C and the gamma-prime solvent temperature plus 25 ° C and for a period of between 1 and 4 hours, an intermediate heat treatment succeeding the hot forging operation which is followed by cooling of the room and carried out at a temperature between the
  • results referred to and previously described are also obtained, according to the invention, by performing at the end of the hot forging operation, i.e. from the moment when the alloy is still at the temperature of forging an isothermal hold at a temperature between the gamma-prime solvent temperature minus 95 ° C and the gamma-prime solvent temperature minus 30 ° C for a period between 1 and 60 minutes.
  • the processing Thermal can be done in two separate stages.
  • the first step consisting of isothermal maintenance at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvent temperature minus 30 ° C is carried out at the end of the forging operation at hot i.e. at the moment when the alloy is still at the forging temperature, for a period between 1 and 30 minutes after which the room is cooled.
  • the second step then consists of a heat treatment carried out at a temperature between the solvent temperature gamma-prime minus 95 ° C and the gamma-prime solvent temperature minus 30 ° C of the superalloy and for a duration included between 1 and 24 hours, followed by heat treatment supersolvus.
  • the alloy M has the following nominal chemical composition in weight percentages:
  • the gamma-prime phase solution temperature or solvent temperature of the alloy is 1195 ° C.
  • the material studied comes from powders atomized with argon and densified by spinning at 1120 ° C.
  • Four rollers A, B, C, D were forged by isothermal forging at 1120 ° C under the conditions of deformation, on the ordinate, and speed of deformation, on the abscissa, represented by the respective curves 1,2,3 and 4 of FIG. 1, thus covering domains greater than 0.1 in deformation and from 10 -4 s -1 to 8.10 -3 s -1 in deformation speed.
  • Other tests have been carried out in traction and are represented by points 5,6,7,8,9,10,11,12 and 13 in FIG. 1.
  • FIG. 2 shows a microstructure with some very large grains obtained after a standard supersolvus heat treatment carried out at 1205 ° C for 4 hours after a tensile test at 1120 ° C corresponding to a deformation rate of 7.10 -3 s -1 and a deformation of 0.62.
  • a sample is subjected to a one hour heat treatment at 1120 ° C. before applying the standard supersolvus heat treatment, as above.
  • Figure 3 shows the microstructure obtained in this case, having smaller grains and showing the appearance of colonies of small grains.
  • microstructure obtained, represented in FIG. 4 is then homogeneous, totally devoid of very large grains and medium size grain is about 50 ⁇ m.
  • the heat treatment process according to the invention therefore provides a state of use of the material concerned with a microstructure ensuring the compromise sought after for the mechanical characteristics of use, especially for parts intended for aeronautical use such as rotating aircraft engine parts, outfit satisfactory in creep and good propagation resistance of cracks at high temperatures.
  • a tensile test piece just after having been deformed under critical conditions leading to the presence of very large grains on the final state namely a temperature of 1120 ° C and a deformation rate of 7.10 -3 s -1 , was maintained at 1120 ° C for 10 minutes.
  • the microstructure obtained is homogeneous and does not have very large grains, as shown in Figure 5.
  • maintaining temperature without intermediate cooling of the room, can be achieved by keeping the part in the tooling forging, at forging temperature.
  • maintaining at the end of the forging operation can be performed in an oven, a temperature between the solvent temperature gamma-prime minus 95 ° C and the gamma-prime solvent temperature minus 30 ° C.

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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)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19970400438 1996-02-29 1997-02-27 Procédé de traitement thermique d'un superalliage à base de nickel Expired - Lifetime EP0792945B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9602534A FR2745588B1 (fr) 1996-02-29 1996-02-29 Procede de traitement thermique d'un superalliage a base de nickel
FR9602534 1996-02-29

Publications (2)

Publication Number Publication Date
EP0792945A1 EP0792945A1 (fr) 1997-09-03
EP0792945B1 true EP0792945B1 (fr) 1998-12-02

Family

ID=9489707

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970400438 Expired - Lifetime EP0792945B1 (fr) 1996-02-29 1997-02-27 Procédé de traitement thermique d'un superalliage à base de nickel

Country Status (6)

Country Link
EP (1) EP0792945B1 (ja)
JP (1) JP3926877B2 (ja)
DE (1) DE69700059T2 (ja)
FR (1) FR2745588B1 (ja)
RU (1) RU2133784C1 (ja)
WO (1) WO1997032052A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102021508A (zh) * 2009-09-15 2011-04-20 通用电气公司 热处理Ni基超合金制品的方法和由其制造的制品

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090000706A1 (en) * 2007-06-28 2009-01-01 General Electric Company Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys
FR2953860B1 (fr) * 2009-12-10 2015-05-15 Snecma Procede de fabrication de superaillages de nickel de type inconel 718
US10563293B2 (en) * 2015-12-07 2020-02-18 Ati Properties Llc Methods for processing nickel-base alloys
KR102193336B1 (ko) * 2017-11-17 2020-12-22 미츠비시 파워 가부시키가이샤 Ni기 단조 합금재 및 그것을 사용한 터빈 고온 부재
RU2697674C1 (ru) * 2019-05-24 2019-08-16 Общество с ограниченной ответственностью "НТЦ "Современные технологии металлургии" (ООО "НТЦ"СТМ") Жаропрочный никелевый сплав
RU2766197C1 (ru) * 2021-07-19 2022-02-09 Акционерное общество "Металлургический завод "Электросталь" Литейный жаропрочный сплав на никелевой основе и изделие, выполненное из него
FR3133623A1 (fr) * 2022-03-17 2023-09-22 Safran Superalliage à base de nickel

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328659A (en) * 1982-10-15 1994-07-12 United Technologies Corporation Superalloy heat treatment for promoting crack growth resistance
CH654593A5 (de) * 1983-09-28 1986-02-28 Bbc Brown Boveri & Cie Verfahren zur herstellung eines feinkoernigen werkstuecks aus einer nickelbasis-superlegierung.
US5393483A (en) * 1990-04-02 1995-02-28 General Electric Company High-temperature fatigue-resistant nickel based superalloy and thermomechanical process
US5413752A (en) * 1992-10-07 1995-05-09 General Electric Company Method for making fatigue crack growth-resistant nickel-base article
US5529643A (en) * 1994-10-17 1996-06-25 General Electric Company Method for minimizing nonuniform nucleation and supersolvus grain growth in a nickel-base superalloy
US5547523A (en) * 1995-01-03 1996-08-20 General Electric Company Retained strain forging of ni-base superalloys

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102021508A (zh) * 2009-09-15 2011-04-20 通用电气公司 热处理Ni基超合金制品的方法和由其制造的制品
CN102021508B (zh) * 2009-09-15 2015-06-03 通用电气公司 热处理Ni基超合金制品的方法和由其制造的制品

Also Published As

Publication number Publication date
JPH1025557A (ja) 1998-01-27
EP0792945A1 (fr) 1997-09-03
FR2745588A1 (fr) 1997-09-05
DE69700059D1 (de) 1999-01-14
FR2745588B1 (fr) 1998-04-30
DE69700059T2 (de) 1999-05-27
JP3926877B2 (ja) 2007-06-06
RU2133784C1 (ru) 1999-07-27
WO1997032052A1 (fr) 1997-09-04

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