EP0825275A1 - Verfahren zur Beschichtung eines Substrates aus Superlegierung auf der Basis Nickel oder Kobalt - Google Patents

Verfahren zur Beschichtung eines Substrates aus Superlegierung auf der Basis Nickel oder Kobalt Download PDF

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Publication number
EP0825275A1
EP0825275A1 EP97401953A EP97401953A EP0825275A1 EP 0825275 A1 EP0825275 A1 EP 0825275A1 EP 97401953 A EP97401953 A EP 97401953A EP 97401953 A EP97401953 A EP 97401953A EP 0825275 A1 EP0825275 A1 EP 0825275A1
Authority
EP
European Patent Office
Prior art keywords
nickel
contribution
cobalt
superalloy
making
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
EP97401953A
Other languages
English (en)
French (fr)
Other versions
EP0825275B1 (de
Inventor
Marie-Caroline Dumez
Jean-Pierre Huchin
Rose Marie Marin-Ayral
Didier Perraud
Jean-Claude Tedenac
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.)
Safran Aircraft Engines SAS
Original Assignee
Sochata
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Filing date
Publication date
Application filed by Sochata filed Critical Sochata
Publication of EP0825275A1 publication Critical patent/EP0825275A1/de
Application granted granted Critical
Publication of EP0825275B1 publication Critical patent/EP0825275B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B22F7/064—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts using an intermediate powder layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the present invention relates to a method for producing a contribution on a part of a turbomachine.
  • FR-A-2 511 908 a process assembly by brazing-diffusion making it possible to report on a nickel or cobalt-based superalloy part a elementary part in the form of a pre-sintered blank formed from a mixture of two powders, one of which, called powder input, is present between 5 and 25% by weight of the mixture and has a nickel, chromium and boron or nickel, cobalt base, silicon and boron.
  • a method of repairing surface defects of parts in superalloy has a plasma flame projection of two successive layers of different compositions, then one heat treatment during which only the first layer is melted and then the surface layer is removed.
  • FR-A-2 511 908 require the use of a homogeneous mixture of powders to prepare a self-brazable sintered material which can be used to produce a contribution by brazing on a localized area of superalloy part.
  • the maximum temperature of use of the superalloy part must remain significantly lower than the brazing temperature.
  • US-4,778,649 describes for example a process for manufacturing a composite material comprising in particular a layer of copper alloy covered with a layer of mixture of Ti + B + Cu powders in which a reaction of synthesis of TiB 2 by combustion self-propagating is triggered by compression and heating. There is thus obtained on a copper substrate, a TiB 2 surface layer and an intermediate layer of a TiB 2 + Cu mixture.
  • Zr or Al as well as other borides or carbides can be used.
  • One of the objects of the invention is to obtain a recharging or a coating of turbomachine parts composed of a nickel-based or cobalt-based superalloy having either a polycrystalline structure, or a structure obtained by directed solidification, i.e. a structure monocrystalline.
  • the installation used for the implementation of the production of a contribution on a superalloy part of turbomachine according to the invention consists of a high pressure supplied with neutral gas by a system of compression and also forming an oven fitted with a heating and temperature measurement.
  • the compressor used is consisting of three compression stages connected in series in which the gas is successively compressed. Pressure final gas reached is 1.5GPa and a pressure gauge controls the value of the gas pressure.
  • the high pressure chamber used includes the fittings suitable for conditions of use at high pressures and high temperatures such as multiple walls inserted in a shield and comprising an envelope of water cooling and all necessary access, electrical connections, gas passage and fittings sealing correspondents. Vacuum equipment about 1Pa is also attached. A rotation of the chamber also allows use in positions horizontal, vertical or inclined.
  • the heating system consists of a heating element under shape of a graphite coil and two electrodes in graphite placed at each end forming an oven placed in said room.
  • the settings allow to ensure a gradient thermal of the order of 200 ° C on a part placed in the oven.
  • Thermocouples are added to allow temperature measurements.
  • Variant embodiments can be made to the installation.
  • Including energy supply equipment used to initiate the reaction can be added as than a tungsten wick, a graphite wick or a laser beam.
  • cleaning operations of the substrate 2 are carried out prior to the installation of the compact element 1 and may include, depending on the condition of the part, new or used, of the degreasing, sanding, chemical deoxidation and / or thermochemical.
  • the compact element 1 can also be obtained depending on the applications by techniques known per se of injection molding.
  • the next step (b) is to introduce the part constituting the substrate 2 carrying the compact element 1 in a hydrostatic neutral gas high pressure chamber a heating enclosure.
  • step (c) makes it possible to carry out a synthesis reaction on the compact element 1 so as to ensure its densification and the metallurgical link between said element 1 and the corresponding surface of the part constituting the substrate 2.
  • the diagram in Figure 2 shows the temperatures measured on the part and shows the ignition temperature of the auto-combustion reaction around 673 ° C.
  • the propagation of a combustion front through the material of compact element 1 upon initiation of the reaction obtained thanks to the temperature gradient of 200 ° C established between the two ends of said element 1 is very fast.
  • the reaction is complete and the propagation speed of the combustion front can be estimated at 20 mm / s.
  • the rate of propagation of the reaction is between 1 and 10cm per second depending on the operating conditions applied.
  • the filler material 1 has macroporosity with good adhesion over the entire length of the affected area of the room 2.
  • NiAl intermetallic material
  • Figures 6 and 7 show the evolution of the concentration of the elements Al, Ni, Co, Cr, Ti along the interphase between materials A and NiAl.
  • a reaction of diffusion between the two materials A and NiAl has produced, the thickness of the interphase reaching about 20 ⁇ m (see zones II and III of figure 4).
  • the interphase obtained is consisting of a continuous solid solution between materials A and NiAl. No intermediate intermetallic compound has been observed.
  • the introduction of chromium into the NiAl phase can justify the increase in hardness of the intermediate phase in zone III by effect of solid solution but the level of hardness confirms the absence of an intermetallic phase complex.
  • step (a) of the process according to the invention the compact element 1 is identical to the one that was used and previously described for example A and it is also obtained from the same way.
  • step (b) the part constituting the substrate 20 carry a sub-layer constituted by the element compact 11 and an outer layer formed by the element compact 1 is introduced into a high pressure chamber hydrostatic neutral gas forming a heating chamber.
  • the next step (c) again makes it possible to carry out a reaction synthesis on compact element 1 and we get a reloading by adding material to the affected area of the room.
  • the micrograph shown in Figure 9 shows the appearance of the material obtained comprising seven zones for which the concentration profiles of the most important elements determined along line 12 are also shown.
  • Zone I corresponds to the NiAl intermetallic material.
  • the homogeneous band of zone II corresponds to the diffusion aluminum and chromium in particular with also a variation of the titanium concentration.
  • zone III the concentrations of Al, Ni, Co and Mo are constant while the concentrations of Cr and Ti vary continuously.
  • Zone IV has a composition close to that of superalloy C with the presence of inclusions of light color corresponding to some variations for certain elements, molybdenum and chromium in particular.
  • Zone VI has a close average composition that of superalloy C with more aluminum and tungsten but less cobalt and silicon. This zone exhibits good homogeneity, the concentrations being all roughly constant.
  • zone VII the concentration of aluminum decreases, while chromium and molybdenum increase continuously.
  • the heat given off by the exothermic reaction of synthesis of the NiAl intermetallic compound is sufficient to affect the entire thickness of the compact sintered element 11 and cause the items to spread to the other side with appearance of an interface between superalloys C and B.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Powder Metallurgy (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97401953A 1996-08-22 1997-08-20 Verfahren zur Beschichtung eines Substrates aus einer Superlegierung auf Nickel- oder Kobaltbasis Expired - Lifetime EP0825275B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9610351 1996-08-22
FR9610351A FR2752540B1 (fr) 1996-08-22 1996-08-22 Procede de realisation d'un apport sur une piece en superalliage a base de nickel ou de cobalt

Publications (2)

Publication Number Publication Date
EP0825275A1 true EP0825275A1 (de) 1998-02-25
EP0825275B1 EP0825275B1 (de) 2001-01-31

Family

ID=9495155

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97401953A Expired - Lifetime EP0825275B1 (de) 1996-08-22 1997-08-20 Verfahren zur Beschichtung eines Substrates aus einer Superlegierung auf Nickel- oder Kobaltbasis

Country Status (6)

Country Link
US (1) US5954895A (de)
EP (1) EP0825275B1 (de)
JP (1) JP4036925B2 (de)
CA (1) CA2207827C (de)
DE (1) DE69704010T2 (de)
FR (1) FR2752540B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2838753A1 (fr) * 2002-04-17 2003-10-24 Snecma Services Procede de realisation d'un apport sur une piece en superalliage a base de nickel ou de cobalt
WO2011131757A1 (fr) 2010-04-23 2011-10-27 Commissariat à l'énergie atomique et aux énergies alternatives Procédé de préparation d'un revêtement multicouche sur une surface d'un substrat par projection thermique

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011087158A1 (de) * 2011-11-25 2013-05-29 Mtu Aero Engines Gmbh Verfahren zur Panzerung der Z-Notch von TiAl-Schaufeln
FR2988736B1 (fr) 2012-04-02 2014-03-07 Onera (Off Nat Aerospatiale) Procede d'obtention d'un revetement d'aluminiure de nickel sur un substrat metallique, et piece munie d'un tel revetement
CN105458269B (zh) * 2015-12-01 2017-12-05 南通大学 一种耐磨涂层的制备方法
US11060194B2 (en) * 2016-12-21 2021-07-13 The United States Of America, As Represented By The Secretary Of The Navy Methods for producing composite structures using diffusion or thermal reactions of a plurality of layers

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB507341A (en) * 1936-12-14 1939-06-14 Inst Physikalische Chemie Der Process for the surface improvement of metals and alloys
GB796531A (en) * 1955-06-30 1958-06-11 Vulliez Paul Improvements in and relating to the surface coating of metals
FR1552850A (de) * 1966-07-05 1969-01-10
JPS5582762A (en) * 1978-12-15 1980-06-21 Hitachi Ltd Heat resistant alloy coating method to provide corrosion and thermal impact resistance
EP0531083A2 (de) * 1991-09-03 1993-03-10 General Electric Company Verfahren, um ein Substrat mit einer harten Oberflächenschicht zu versehen
EP0574290A1 (de) * 1992-06-05 1993-12-15 Gec Alsthom Electromecanique Sa Verfahren zum Anbringen von Schutzüberzügen bildenden Einsätzen auf Gegenständen aus martensitischens Stahl oder aus Titanlegierungen
US5352539A (en) * 1992-10-27 1994-10-04 Friedrich Theysohn Gmbh Extruder housing for double-screw extruder having an annularly stepped internal bore covered by a hot isostatically-pressed structure, and method of making same

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4219592A (en) * 1977-07-11 1980-08-26 United Technologies Corporation Two-way surfacing process by fusion welding
FR2511908A1 (fr) * 1981-08-26 1983-03-04 Snecma Procede de brasage-diffusion destine aux pieces en superalliages
US4705203A (en) * 1986-08-04 1987-11-10 United Technologies Corporation Repair of surface defects in superalloy articles
JPS6342859A (ja) * 1986-08-08 1988-02-24 航空宇宙技術研究所長 傾斜機能材料の製造方法
JPH0613743B2 (ja) * 1987-11-19 1994-02-23 工業技術院長 ニッケル基超合金の固相接合法
US5330701A (en) * 1992-02-28 1994-07-19 Xform, Inc. Process for making finely divided intermetallic
US5342539A (en) * 1993-02-08 1994-08-30 Diatec Polymers Polyacrylamide-phosphonate flocculants and methods of making
US5837385A (en) * 1997-03-31 1998-11-17 General Electric Company Environmental coating for nickel aluminide components and a method therefor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB507341A (en) * 1936-12-14 1939-06-14 Inst Physikalische Chemie Der Process for the surface improvement of metals and alloys
GB796531A (en) * 1955-06-30 1958-06-11 Vulliez Paul Improvements in and relating to the surface coating of metals
FR1552850A (de) * 1966-07-05 1969-01-10
JPS5582762A (en) * 1978-12-15 1980-06-21 Hitachi Ltd Heat resistant alloy coating method to provide corrosion and thermal impact resistance
EP0531083A2 (de) * 1991-09-03 1993-03-10 General Electric Company Verfahren, um ein Substrat mit einer harten Oberflächenschicht zu versehen
EP0574290A1 (de) * 1992-06-05 1993-12-15 Gec Alsthom Electromecanique Sa Verfahren zum Anbringen von Schutzüberzügen bildenden Einsätzen auf Gegenständen aus martensitischens Stahl oder aus Titanlegierungen
US5352539A (en) * 1992-10-27 1994-10-04 Friedrich Theysohn Gmbh Extruder housing for double-screw extruder having an annularly stepped internal bore covered by a hot isostatically-pressed structure, and method of making same

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 4, no. 129 (C - 024) 10 September 1980 (1980-09-10) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2838753A1 (fr) * 2002-04-17 2003-10-24 Snecma Services Procede de realisation d'un apport sur une piece en superalliage a base de nickel ou de cobalt
WO2011131757A1 (fr) 2010-04-23 2011-10-27 Commissariat à l'énergie atomique et aux énergies alternatives Procédé de préparation d'un revêtement multicouche sur une surface d'un substrat par projection thermique

Also Published As

Publication number Publication date
DE69704010D1 (de) 2001-03-08
CA2207827A1 (fr) 1998-02-22
EP0825275B1 (de) 2001-01-31
CA2207827C (fr) 2004-06-15
FR2752540A1 (fr) 1998-02-27
FR2752540B1 (fr) 1998-12-04
DE69704010T2 (de) 2001-06-21
JPH10237507A (ja) 1998-09-08
US5954895A (en) 1999-09-21
JP4036925B2 (ja) 2008-01-23

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