EP0148688A2 - Verfahren zur thermomechanischen Behandlung von Superlegierungen, um Gefüge mit guten mechanischen Eigenschaften zu erhalten - Google Patents

Verfahren zur thermomechanischen Behandlung von Superlegierungen, um Gefüge mit guten mechanischen Eigenschaften zu erhalten Download PDF

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Publication number
EP0148688A2
EP0148688A2 EP84402647A EP84402647A EP0148688A2 EP 0148688 A2 EP0148688 A2 EP 0148688A2 EP 84402647 A EP84402647 A EP 84402647A EP 84402647 A EP84402647 A EP 84402647A EP 0148688 A2 EP0148688 A2 EP 0148688A2
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EP
European Patent Office
Prior art keywords
sequence
deformation
final
phase
heat treatment
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EP84402647A
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English (en)
French (fr)
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EP0148688A3 (en
EP0148688B1 (de
Inventor
Alain Roger Leonnard
Janick Jean-Marie Lucien Leray
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0148688A3 publication Critical patent/EP0148688A3/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 thermomechanical treatment process applicable to superalloys and making it possible to obtain structures with high mechanical characteristics.
  • a too low reheating temperature leads to the conservation of the fine structure due to the previous sequence, with however, precipitation of the Ni 3 Nb - ⁇ phase in the grain boundaries or, for certain conditions, inside the grains, in the form of platelets increasing preferentially in the crystallographic planes of the type ⁇ 111 ⁇ .
  • the phase ⁇ of orthorhombic structure, is harmful whatever its morphology because it fixes niobium and thus limits the formation of the hardening phase Ni 3 Nb - ⁇ "(gamma second), metastable, of centered quadratic structure.
  • the heating before forging at a too high temperature avoids the precipitation of phase ⁇ in platelets, but leads on the other hand to an increase in the grain size, detrimental to the resistance to fatigue.
  • the advantage of the process according to the invention stems from the possibility of obtaining fine-grained structures, according to heating / forging sequences simultaneously guaranteeing the absence of phase platelets and the existence of a residual work hardening essential for consolidation of the alloy.
  • U.S.-A-3,660,177 proposes a grain refinement method based on the precipitation of the Ni3 Nb - - phase within the grains before the forging operation and the recrystallization treatment.
  • the precipitation treatment of phase ⁇ carried out at around 900 ° C, before forging, leads to a subdivision of the grains by platelets of phase ⁇ which form in planes of type ⁇ 111 ⁇ .
  • the heat treatment, carried out after forging with a reduction in thickness of 50 to 65% leads to globulation of the deformed wafers of phase e and recrystallization of the structure.
  • This process makes it possible to obtain recrystallized structures, of 10 ASTM or more called "Minigrain", whose fatigue characteristics are improved, but whose creep resistance and tenacity are notoriously insufficient for a material with high characteristics, necessary for certain industrial applications.
  • a deformation rate of between 30% and 60%, preferably 45%, is achieved during the hot deformation by compression operation entering the final roughing sequence, then a deformation rate of the order of 8% to 25% is carried out in the same way in the finishing sequence.
  • the parasitic phase is a Ni 3 Nb type 0 phase in the form of platelets.
  • the heating conditions in the final roughing sequence are 1040 ° C ⁇ 10 ° C for fifty minutes and the maintenance isothermal is carried out at 970 ° C for thirty minutes.
  • the structure obtained is moreover more homogeneous, following a reduction of the dead zones: in fact, the roller parts which cool prematurely in contact with the tool, present, before isothermal maintenance, a work hardened structure and grains of recrystallization, the migration of the joints of which has been hindered by cooling to temperatures below the recrystallization range. Isothermal maintenance then allows the microstructure to evolve by generalizing recrystallization to the largest part of the part: the dead zones are therefore reduced and the structure refined, since the grain size of the internal parts of the roller goes for example from 3 1/2 ASTM to 8 - 8 1/2 AST after 45% or 60% of wrought.
  • the recrystallization grain goes from 8 to 6-6.5 ASTM, the intermediate temperature 970 ° C-conferring a fine and homogeneous structure, with a grain size of about 8 ASTM ( Figures 4 to 6A ).
  • the Niobium element is used entirely for the formation of the hardening phase Ni 3 Nb - ⁇ "; only a few seeds of Ni 3 Nb - ⁇ phase can sometimes be detected by microscopy at high magnification The low volume fraction of these germs and their globular morphology then have no detrimental impact on the mechanical properties.
  • One of the characteristics of the invention is to retain, for the final deformation, deformation rates not exceeding 25%.
  • a homogeneous structure of 8 ASTMs is then obtained, the grains of which have the particularity of being provided with a network of dislocations which tend, in part, to rearrange into a very fine substructure ( ⁇ 15 ASTM) also hardened, at in the vicinity of the deformed grain boundaries (see Figures 7 to 8A).
  • ⁇ 15 ASTM very fine substructure
  • the first solution (a) consists in allowing the raw, forged parts to cool in the open air on refractory plates, without stacking them. After cooling, the parts undergo a heat treatment limited to the income R of precipitation of the phase ⁇ ".
  • the forged piece is placed directly in an oven, without going through the ambient temperature, to undergo the treatment of tempering R.
  • the tempering treatment applied is one of the known treatments and consists of maintaining for eight hours at 720 ° C followed by cooling at the speed of 50 ° C per hour to 620 ° C with maintenance eight hours at 620 ° C, terminated by air cooling.
  • thermomechanical range object of the invention, made it possible to obtain at the end of the foogging, a hardened structure, with fine grains, free of ⁇ phase in platelets.
  • the treatment T 955 ° C - 1 h - air was voluntarily excluded from the ranges offered. Indeed, the latter whose role was to ensure the homogenization of the alloy, before the treatment - R - of precipitation of the ⁇ phase ", leads in fact, on the one hand to the more or less marked precipitation of platelets ⁇ phase and, on the other hand, to a heterogeneous recrystallization, at the origin of a deconsolidation of the alloy.
  • the residual work hardening obtained by the invention makes it possible, among other things, to facilitate under certain conditions the germination of a minor phase such as Ni 3 Nb - ⁇ or ⁇ ". Taking into account the objective which returns to avoid the precipitation of phase ⁇ , it is thus necessary to suppress the treatment T whose temperature belongs to the domain of existence of phase ⁇ .
  • the application of income makes it possible to preserve work hardening residual of the structure; moreover, the tempering temperature range (720-620 ° C) corresponds to the unique precipitation of the hardening phase ⁇ ".
  • the rough part presents a homogeneous, fine-grained structure.
  • the part is taken out of the oven to be directly crushed with a deformation rate of 8 to 25%.
  • This low rate of deformation constitutes an important advantage of the method: it makes it possible to use less powerful tools, therefore more readily available and less expensive.
  • Air cooling can be carried out either at the end of forging, or at the end of the final heat treatment, on a refractory hearth (to avoid excessively rapid heat exchanges).
  • oligocyclic fatigue tests with imposed total longitudinal deformation were carried out at 650 ° C according to a triangular cycle of frequency 0.05 Hz with: where ⁇ lt is the total longitudinal deformation (elastic + plastic).

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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)
  • Superconductors And Manufacturing Methods Therefor (AREA)
EP84402647A 1983-12-21 1984-12-19 Verfahren zur thermomechanischen Behandlung von Superlegierungen, um Gefüge mit guten mechanischen Eigenschaften zu erhalten Expired EP0148688B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8320436 1983-12-21
FR8320436A FR2557145B1 (fr) 1983-12-21 1983-12-21 Procede de traitements thermomecaniques pour superalliages en vue d'obtenir des structures a hautes caracteristiques mecaniques

Publications (3)

Publication Number Publication Date
EP0148688A2 true EP0148688A2 (de) 1985-07-17
EP0148688A3 EP0148688A3 (en) 1985-08-14
EP0148688B1 EP0148688B1 (de) 1988-10-12

Family

ID=9295378

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84402647A Expired EP0148688B1 (de) 1983-12-21 1984-12-19 Verfahren zur thermomechanischen Behandlung von Superlegierungen, um Gefüge mit guten mechanischen Eigenschaften zu erhalten

Country Status (5)

Country Link
US (1) US4614550A (de)
EP (1) EP0148688B1 (de)
JP (1) JPS60155658A (de)
DE (1) DE3474571D1 (de)
FR (1) FR2557145B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0720177A1 (de) * 1994-12-29 1996-07-03 Framatome Verfahren zur Fertigung eines Rohrs für Kernbrennstabbündel und danach erhaltene Rohre

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0868237B1 (de) * 1995-12-14 2000-04-12 Attlington Investments Limited Verfahren zur herstellung eines metallprofils
US6193823B1 (en) * 1999-03-17 2001-02-27 Wyman Gordon Company Delta-phase grain refinement of nickel-iron-base alloy ingots
EP1325965B1 (de) * 2001-12-21 2005-10-05 Hitachi Metals, Ltd. Ni-Legierung mit verbesserter Oxidations- Resistenz, Warmfestigkeit and Warmbearbeitbarkeit
US20040221929A1 (en) 2003-05-09 2004-11-11 Hebda John J. Processing of titanium-aluminum-vanadium alloys and products made thereby
US7520947B2 (en) * 2003-05-23 2009-04-21 Ati Properties, Inc. Cobalt alloys, methods of making cobalt alloys, and implants and articles of manufacture made therefrom
US7156932B2 (en) * 2003-10-06 2007-01-02 Ati Properties, Inc. Nickel-base alloys and methods of heat treating nickel-base alloys
US7837812B2 (en) 2004-05-21 2010-11-23 Ati Properties, Inc. Metastable beta-titanium alloys and methods of processing the same by direct aging
US7531054B2 (en) * 2005-08-24 2009-05-12 Ati Properties, Inc. Nickel alloy and method including direct aging
US7985304B2 (en) * 2007-04-19 2011-07-26 Ati Properties, Inc. Nickel-base alloys and articles made therefrom
US10053758B2 (en) 2010-01-22 2018-08-21 Ati Properties Llc Production of high strength titanium
US9255316B2 (en) 2010-07-19 2016-02-09 Ati Properties, Inc. Processing of α+β titanium alloys
US9206497B2 (en) 2010-09-15 2015-12-08 Ati Properties, Inc. Methods for processing titanium alloys
US8613818B2 (en) 2010-09-15 2013-12-24 Ati Properties, Inc. Processing routes for titanium and titanium alloys
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
US8652400B2 (en) 2011-06-01 2014-02-18 Ati Properties, Inc. Thermo-mechanical processing of nickel-base alloys
US9869003B2 (en) 2013-02-26 2018-01-16 Ati Properties Llc Methods for processing alloys
US9192981B2 (en) 2013-03-11 2015-11-24 Ati Properties, Inc. Thermomechanical processing of high strength non-magnetic corrosion resistant material
US9777361B2 (en) 2013-03-15 2017-10-03 Ati Properties Llc Thermomechanical processing of alpha-beta titanium alloys
US11111552B2 (en) 2013-11-12 2021-09-07 Ati Properties Llc Methods for processing metal alloys
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys
US10563293B2 (en) 2015-12-07 2020-02-18 Ati Properties Llc Methods for processing nickel-base alloys
CN111719039B (zh) * 2019-03-22 2022-05-24 上海电气电站设备有限公司 一种FeCoNiAlNb高温合金均匀化处理方法
US12344918B2 (en) 2023-07-12 2025-07-01 Ati Properties Llc Titanium alloys

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE756653A (fr) * 1969-09-26 1971-03-01 United Aircraft Corp Accroissement thermo-mecanique de la resistance des superalliages (
US3676225A (en) * 1970-06-25 1972-07-11 United Aircraft Corp Thermomechanical processing of intermediate service temperature nickel-base superalloys
FR2154871A5 (de) * 1971-09-28 1973-05-18 Creusot Loire
US3871928A (en) * 1973-08-13 1975-03-18 Int Nickel Co Heat treatment of nickel alloys
JPS57101634A (en) * 1980-12-12 1982-06-24 Hitachi Ltd Ni base alloy with superior stress corrosion resisting property and manufacture thereof
JPS59211560A (ja) * 1983-05-18 1984-11-30 Hitachi Ltd 原子炉用Ｎｉ基合金の熱処理方法

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0720177A1 (de) * 1994-12-29 1996-07-03 Framatome Verfahren zur Fertigung eines Rohrs für Kernbrennstabbündel und danach erhaltene Rohre
FR2729000A1 (fr) * 1994-12-29 1996-07-05 Framatome Sa Procede de fabrication d'un tube pour assemblage de combustible nucleaire et tubes conformes a ceux ainsi obtenus

Also Published As

Publication number Publication date
DE3474571D1 (en) 1988-11-17
EP0148688A3 (en) 1985-08-14
EP0148688B1 (de) 1988-10-12
FR2557145B1 (fr) 1986-05-23
JPS60155658A (ja) 1985-08-15
US4614550A (en) 1986-09-30
FR2557145A1 (fr) 1985-06-28

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