EP0825275B1 - Verfahren zur Beschichtung eines Substrates aus einer Superlegierung auf Nickel- oder Kobaltbasis - Google Patents

Verfahren zur Beschichtung eines Substrates aus einer Superlegierung auf Nickel- oder Kobaltbasis Download PDF

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Publication number
EP0825275B1
EP0825275B1 EP97401953A EP97401953A EP0825275B1 EP 0825275 B1 EP0825275 B1 EP 0825275B1 EP 97401953 A EP97401953 A EP 97401953A EP 97401953 A EP97401953 A EP 97401953A EP 0825275 B1 EP0825275 B1 EP 0825275B1
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EP
European Patent Office
Prior art keywords
base
article
layer
nickel
cobalt
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.)
Expired - Lifetime
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EP97401953A
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English (en)
French (fr)
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EP0825275A1 (de
Inventor
Marie-Caroline Dumez
Jean-Pierre Huchin
Rose Marie Marin-Ayral
Didier Perraud
Jean-Claude Tedenac
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Safran Aircraft Engines SAS
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SNECMA Services SA
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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.
  • GB.507,341 A describes a process for producing a layer of a compound intermetallic to the surface of a metal substrate by submitting a plunged part in a powder bed to a diffusion treatment.
  • FR-A-2 511 908 require the use of a homogeneous mixture of powders to prepare a self-brazing 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.

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  • 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)

Claims (7)

  1. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis,
       dadurch gekennzeichnet, dass es die folgenden, aufeinanderfolgenden Verfahrensschritte aufweist:
    (a) Ablagerung eines Beschichtungselements (1; 1, 11) einerseits aus der Gruppe der Pulver, die in den Proportionen reagieren, die der Bildung eines intermetallischen Stoffes entsprechen, und andererseits aus der Gruppe der Superlegierungs-Pulver auf Nickel- oder Kobaltbasis, in mindestens einem bestimmten Bereich des Werkstücks (2; 20);
    (b) Einbringen des Werkstücks (2; 20), auf dem die Ablagerung in Schritt (a) vorgenommen wurde, in eine Hochdruckkammer, die durch ein Drucksystem dergestalt mit einem neutralen Gas gespeist wird, dass in der Kammer ein hydrostatischer Druck des neutralen Gases von bis zu 1,5 Gpa gewährleistet werden kann, wobei diese Kammer auch einen Ofen bildet, der mit Heizelementen ausgestattet ist, durch die eine Temperatur von 1200 °C erreicht werden kann, und zwar mit einer Temperaturanstiegsgeschwindigkeit von 5 °C/min bis 120 °C/min, wobei von einem Ende des betreffenden Werkstückbereichs (2; 20) zum anderen ein Temperaturgradient von 200 °C gewährleistet ist, und wobei die Temperaturen mit einem Messsystem überwacht werden;
    (c) Durchführung einer Synthese-Reaktion durch selbstausbreitende Verbrennung unter hohem hydrostatischen Gasdruck an dem genannten Beschichtungselement unter bestimmten Temperatur- und Druckbedingungen dergestalt, dass die Verdichtung der Beschichtung (1; 1, 11) und die metallurgische Verbindung zwischen dieser Beschichtung und der betroffenen Oberfläche des Superlegierungs-Teils gewährleistet ist.
  2. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach Anspruch 1; wobei diese Beschichtung eine Ausbesserung eines bestimmten Werkstückbereichs darstellt und der Verfahrensschritt (c), der durch ein einfaches Abkühlen des Werkstücks abgeschlossen wird, von einer Fertigbearbeitung der Oberflächen durch einen Feinbearbeitungsvorgang gefolgt wird.
  3. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach Anspruch 1, wobei diese Beschichtung einen Schutzüberzug über mindestens einen Bereich des Werkstücks darstellt, wodurch die Festigkeit gegen Oxidation, Korrosion und/oder Erosion erhöht werden kann.
  4. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach einem der Ansprüche 1 bis 3, wobei die endgültige Dicke der auf dem Werkstück hergestellten Ablagerung zwischen 20 µm und 10 mm beträgt.
  5. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach einem der Ansprüche 1, 2 und 4, wobei die Ablagerung in Verfahrensschritt (a) hergestellt wird, indem ein kompaktes Element (1) aufgebracht wird, das aus der Mischung der adäquaten Mengen von Nickel- und Aluminiumpulver mit einer Korngröße von weniger als 150 µm, mit gleichen Atomanteilen hergestellt wird, wobei diese Mischung in eine geeignete Form gefüllt wird und unter einer Belastung von 40 MPa kaltgepresst wird.
  6. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach Anspruch 5, wobei in Verfahrensschritt (a) beim Aufbringen des kompakten Elements (1) ein weiteres, kompaktes Zusatzelement (11) als Unterschicht auf die Oberfläche des betreffenden Bereichs des das Substrat (20) bildenden Werkstücks eingefügt wird, wobei dieses Zusatzelement (11) zuvor durch Sintern von Superlegierungspulvern auf Nickelbasis hergestellt wird.
  7. Verfahren zur Beschichtung eines Werkstücks aus einer Superlegierung auf Nickel- oder Kobaltbasis nach Anspruch 6, wobei die Superlegierung des das Substrat (20) bildenden Werkstücks die folgende nominale Zusammensetzung in Gewichtsanteilen aufweist:
    Ni Basis, Cr 14; Co 9,5; Mo 4; Al 3; W 4; Ti 5; Si 0,2, Mn 0,2; C 0,17 und das kompakte Zusatzelement (11) die folgende Zusammensetzung in Gewichtsanteilen aufweist:
    Ni Basis; Co 16,5 bis 19; Cr 10,4 bis 12,2; Mo 3,3 bis 4,2; Al 2,85 bis 3,15; Ti 2,45 bis 2,8; Si 1 bis 1,3; B 0,68 bis 0,8; C 0 bis 0,06.
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
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
FR9610351 1996-08-22

Publications (2)

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

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

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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)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2838753B1 (fr) * 2002-04-17 2004-05-28 Snecma Services Procede de realisation d'un apport sur une piece en superalliage a base de nickel ou de cobalt
FR2959244B1 (fr) 2010-04-23 2012-06-29 Commissariat Energie Atomique Procede de preparation d'un revetement multicouche sur une surface d'un substrat par projection thermique.
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

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
FR830779A (fr) * 1936-12-14 1938-08-09 Inst Fu R Physikalische Chemie Procédé pour améliorer la surface de métaux et d'alliages
FR1216207A (fr) * 1955-06-30 1960-04-22 Perfectionnements aux procédés de formation d'alliages superficiels par diffusion en phase gazeuse d'un métal d'apport
US3450512A (en) * 1966-07-05 1969-06-17 United Aircraft Corp Coated nickel base engine alloys
US4219592A (en) * 1977-07-11 1980-08-26 United Technologies Corporation Two-way surfacing process by fusion welding
JPS5582762A (en) * 1978-12-15 1980-06-21 Hitachi Ltd Heat resistant alloy coating method to provide corrosion and thermal impact resistance
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
US5812926A (en) * 1991-09-03 1998-09-22 General Electric Company Process for hard facing a substrate
US5330701A (en) * 1992-02-28 1994-07-19 Xform, Inc. Process for making finely divided intermetallic
EP0574290B1 (de) * 1992-06-05 1996-04-17 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
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

Also Published As

Publication number Publication date
CA2207827C (fr) 2004-06-15
CA2207827A1 (fr) 1998-02-22
JPH10237507A (ja) 1998-09-08
DE69704010T2 (de) 2001-06-21
FR2752540A1 (fr) 1998-02-27
JP4036925B2 (ja) 2008-01-23
FR2752540B1 (fr) 1998-12-04
EP0825275A1 (de) 1998-02-25
DE69704010D1 (de) 2001-03-08
US5954895A (en) 1999-09-21

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