EP0792945A1 - Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis - Google Patents

Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis Download PDF

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Publication number
EP0792945A1
EP0792945A1 EP97400438A EP97400438A EP0792945A1 EP 0792945 A1 EP0792945 A1 EP 0792945A1 EP 97400438 A EP97400438 A EP 97400438A EP 97400438 A EP97400438 A EP 97400438A EP 0792945 A1 EP0792945 A1 EP 0792945A1
Authority
EP
European Patent Office
Prior art keywords
temperature
gamma
superalloy
prime
minus
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.)
Granted
Application number
EP97400438A
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English (en)
French (fr)
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EP0792945B1 (de
Inventor
Yves Philippe Marc Desvallees
Jean-Michel Patrick Maurice Franchet
Michel Marty
Henri Octor
Françoise Passilly
Michèle Soucail
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.)
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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Application filed by Office National dEtudes et de Recherches Aerospatiales ONERA, Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Office National dEtudes et de Recherches Aerospatiales ONERA
Publication of EP0792945A1 publication Critical patent/EP0792945A1/de
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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 the thermal 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; Neither complement to 100, ie at the request FR 95.09653 and belongs to the following domain: 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 disks.
  • parts of this type can in particular be produced using processing techniques from powders and their shaping calls for forging operations.
  • the heat treatments applied to the parts before use commonly comprise a solution and quenching treatment followed by an aging treatment.
  • the invention applies in particular in cases where a supersolvus heat treatment is carried out comprising complete dissolution of the gamma-prime precipitates at a temperature between + 5 ° C and + 25 ° C above the solvent temperature gamma-prime for a hold time of between 1 hour and 4 hours.
  • the final grain size depends on a succession of industrial stages which are: the possible pretreatment of the powders, densification by spinning, isothermal forging, the final heat treatment.
  • the metallurgical and thermomechanical parameters that can influence recrystallization are numerous and interdependent. These include: gamma-prime phase precipitation, oxycarbon distribution, strain rate, strain rate, 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.
  • an intermediate heat treatment succeeding the hot forging operation which is followed by cooling of the part and carried out at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvus temperature minus 30 ° C and between 1 and 24 hours.
  • results referred to and previously described are also obtained, in accordance with the invention, by carrying out at the end of the hot forging operation, that is to say from the moment when the alloy is still at the forging temperature isothermal maintenance at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvus temperature minus 30 ° C for a period of between 1 and 60 minutes.
  • the heat treatment can be carried out in two distinct stages.
  • the first step consisting of isothermal maintenance at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvus temperature minus 30 ° C is carried out at the end of the hot forging operation c '' is to say at the moment when the alloy is still at the forging temperature, for a period of between 1 and 30 minutes after which, the part is cooled.
  • the second step then consists of a heat treatment carried out at a temperature between the gamma-prime solvus temperature minus 95 ° C and the gamma-prime solvus temperature minus 30 ° C of the superalloy and for a period of between 1 and 24 hours, followed by a supersolvus heat treatment.
  • 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.
  • the microstructure obtained, represented in FIG. 4 is then homogeneous, completely devoid of very large grains and the average size of the grains is around 50 ⁇ m.
  • the heat treatment method according to the invention therefore makes it possible to obtain a state of use of the material concerned having a microstructure ensuring the compromise sought for the mechanical characteristics of use, in particular for parts intended for aeronautical use such as rotating aircraft engine parts, satisfactory creep resistance and good crack propagation resistance 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.
  • temperature maintenance without intermediate cooling of the part, can be achieved by keeping the part in the forging tool at the forging temperature.
  • the maintenance at the end of the forging operation can be carried out in an oven, at a temperature between the gamma-prime solvus temperature minus 95 ° C. and the gamma-solvus temperature. prime 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 Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis Expired - Lifetime EP0792945B1 (de)

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 true EP0792945A1 (de) 1997-09-03
EP0792945B1 EP0792945B1 (de) 1998-12-02

Family

ID=9489707

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970400438 Expired - Lifetime EP0792945B1 (de) 1996-02-29 1997-02-27 Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis

Country Status (6)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011070302A1 (fr) * 2009-12-10 2011-06-16 Snecma Procede de fabrication de superalliages de nickel de type inconel 718

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6908519B2 (en) * 2002-07-19 2005-06-21 General Electric Company Isothermal forging of nickel-base superalloys in air
US6932877B2 (en) * 2002-10-31 2005-08-23 General Electric Company Quasi-isothermal forging of a nickel-base superalloy
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
US8313593B2 (en) * 2009-09-15 2012-11-20 General Electric Company Method of heat treating a Ni-based superalloy article and article made thereby
US10563293B2 (en) * 2015-12-07 2020-02-18 Ati Properties Llc Methods for processing nickel-base alloys
KR102214684B1 (ko) * 2017-11-17 2021-02-10 미츠비시 파워 가부시키가이샤 Ni기 단조 합금재의 제조 방법
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0142668A1 (de) * 1983-09-28 1985-05-29 BBC Aktiengesellschaft Brown, Boveri & Cie. Verfahren zur Herstellung eines feinkörnigen Werkstücks aus einer Nickelbasis-Superlegierung
US5328659A (en) * 1982-10-15 1994-07-12 United Technologies Corporation Superalloy heat treatment for promoting crack growth resistance
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

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE794144A (fr) * 1972-01-17 1973-07-17 Int Nickel Ltd Alliages de nickel-chrome
US4624716A (en) * 1982-12-13 1986-11-25 Armco Inc. Method of treating a nickel base alloy
SU1744143A1 (ru) * 1989-04-11 1992-06-30 Производственное объединение "Южный машиностроительный завод" Способ обработки заготовок из жаропрочных дисперсионно-твердеющих сплавов на основе никел
US5061324A (en) * 1990-04-02 1991-10-29 General Electric Company Thermomechanical processing for fatigue-resistant nickel based superalloys

Patent Citations (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
EP0142668A1 (de) * 1983-09-28 1985-05-29 BBC Aktiengesellschaft Brown, Boveri & Cie. Verfahren zur Herstellung eines feinkörnigen Werkstücks 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 (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011070302A1 (fr) * 2009-12-10 2011-06-16 Snecma Procede de fabrication de superalliages de nickel de type inconel 718
FR2953860A1 (fr) * 2009-12-10 2011-06-17 Snecma Procede de fabrication de superaillages de nickel de type inconel 718
CN102652179A (zh) * 2009-12-10 2012-08-29 斯奈克玛 一种制造铬镍铁耐热蚀合金718型镍超级合金的方法
CN102652179B (zh) * 2009-12-10 2015-11-25 斯奈克玛 一种制造铬镍铁耐热蚀合金718型镍超级合金的方法

Also Published As

Publication number Publication date
WO1997032052A1 (fr) 1997-09-04
JPH1025557A (ja) 1998-01-27
DE69700059D1 (de) 1999-01-14
JP3926877B2 (ja) 2007-06-06
FR2745588A1 (fr) 1997-09-05
RU2133784C1 (ru) 1999-07-27
FR2745588B1 (fr) 1998-04-30
DE69700059T2 (de) 1999-05-27
EP0792945B1 (de) 1998-12-02

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