EP0166940A2 - Couche de rodage d'une turbomachine - Google Patents

Couche de rodage d'une turbomachine Download PDF

Info

Publication number
EP0166940A2
EP0166940A2 EP85106255A EP85106255A EP0166940A2 EP 0166940 A2 EP0166940 A2 EP 0166940A2 EP 85106255 A EP85106255 A EP 85106255A EP 85106255 A EP85106255 A EP 85106255A EP 0166940 A2 EP0166940 A2 EP 0166940A2
Authority
EP
European Patent Office
Prior art keywords
covering according
particles
covering
core
shell
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
EP85106255A
Other languages
German (de)
English (en)
Other versions
EP0166940A3 (en
EP0166940B1 (fr
Inventor
Wilhelm Hoffmüller
Josef Eichner
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0166940A2 publication Critical patent/EP0166940A2/fr
Publication of EP0166940A3 publication Critical patent/EP0166940A3/de
Application granted granted Critical
Publication of EP0166940B1 publication Critical patent/EP0166940B1/fr
Expired legal-status Critical Current

Links

Images

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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/11—Making porous workpieces or articles
    • B22F3/1103—Making porous workpieces or articles with particular physical characteristics
    • B22F3/1112—Making porous workpieces or articles with particular physical characteristics comprising hollow spheres or hollow fibres
    • 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
    • B22F7/002—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 porous nature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps

Definitions

  • the object of the invention is to develop a relatively soft / soft coating which allows the minimization of the radial gap between the rotor blades and the housing of a turbomachine, such as a compressor, and yet has a low sensitivity to temperature and erosion.
  • the groups with the ceramic or glass-containing core of the particles of the composite material result in better insulation of the covering from the housing.
  • the application temperature is not limited by the core material, but only by the enveloping material. Since it is metallic, it can be easily connected and compacted. The material consumption during the production of the layered composite material and / or its application is significantly lower than in the conventional spraying process.
  • the core and shell formation of the particles has the particular advantage that the metallic part of the composite material ESP-775 overall can be kept lower than in the case of known inlet linings, which in particular reduces the harmful influence of abraded material in the turbine (for example sticking of cooling air bores, less erosion of subsequent turbine stages and less environmental pollution).
  • the core is non-metallic
  • the shell is metallic.
  • Metallic is understood to mean a metal-containing material, be it a compound, a mixture or the like.
  • the metallic components of the shell allow the powder particles to bond well after sintering.
  • sintering can also be applied serve the coating on the inside of the housing wall in which the powder is introduced between two rings, one of which is the said inner wall of the housing. Sintering takes place in a conventional manner in an oven known per se.
  • Fig. 1 is a spherical particle with a ceramic core 1, such as BN, Zr0 2 -, A1 2 0 3 - or graphite core and a metallic sleeve 2, for example made of nickel, aluminum or Ni-Al, Ni-Cr, Ni -Mo, Ni-Co, Ni-Ti, Ni-Cu alloys.
  • Nickel is preferably used as a cladding material, because the operating temperature without damaging oxidation is very high (in the range of about 500 ° C +/- 5 0 0 C).
  • a graphite core is preferred because graphite is an ideal lubricant for bearings and has proven its worth in seals.
  • the particles according to FIG. 1 can, for example, be spherical and have a diameter between approximately 50 and 150 ⁇ m.
  • the hardness of the coating produced by particles sintered together is mainly dependent on the size and / or quantity of the graphite of the core and the shell material used and its quantity or thickness. If a high temperature resistance of the inlet lining is required, the nickel can be alloyed with a higher alloy.
  • the volume part of the core 1 in the particle is advantageously about 75%.
  • the thickness of the shell 2 is about 1-5 ⁇ m on the core, however only about 1/3 by weight.
  • the particles are advantageously sintered together at low pressure, from about C -1 M Pa and a temperature, in a vacuum oven, from about 1000 ° C to about 1500 ° C and a time of a few hours. It is advantageous if the powder to be sintered is filled into molds which have the outer dimensions of the coating to be inserted into the housing rings. Of course, the shapes can be removed again after the sintering, for example as radially inner rings. The inner wall of the housing, which is preferably cooled, is then used as the outer ring, as is known per se.
  • the metallic casing material so that it can be easily peeled off from a compressor or turbine blade of an engine. It must also be taken into account here that most known blade materials lose their hardness at high temperatures. In other words, they become very hot when rubbed against the running-in surface and at the same time their wear resistance decreases. This suggests if the operating temperature (operating temperature) permits the use of aluminum or copper-nickel as the shell material.
  • the layered composite material made of particles can still be compressed by rolling or rolling to form a dense, smooth covering which is very erosion and corrosion-resistant, even at the operating temperatures mentioned. Any remaining porosity, especially on the surface of a layered composite material for the covering, can also be eliminated by infiltrating metals, glasses, enamel.
  • FIG. 2 shows a hollow sphere which, as in FIG. 1, can be filled with graphite, but also from Al 2 O 3 -, ZrO 2 - or the like as oxide ceramic, a glass or glass-containing or Si0 2 - containing core 4 can exist. So-called glass ceramics or metallic glasses are also well suited. Composites made of particles with small ceramic balls or grains result in better thermal insulation of the covering to the housing.
  • the size and amount of the core material is the same or similar to that in FIG. 1 and the materials used for the casing 2 are the same as those in FIG. 1.
  • the core is coated with the shell materials in several layers 2a, 2b, likewise by galvanic means or by means of PVD or CVD processes.
  • the thickness of the layers is of the same order of magnitude.
  • the process conditions for the sintering should be the same or similar to those in FIG. 1. Post-compaction or smoothing of the surface by infiltration can also be carried out as described there.
  • FIG. 3 shows a micrograph through a sintered sealing covering made of composite material.
  • the intimate connection of the particles, such as balls or grains, to one another means that erosion, for example caused by aggressive gas from a gas turbine, is not possible.
  • Fig. 3 shows that the pure spherical shape is essentially only in the starting material (powder). Any grain shape can be present after sintering.
  • Figure 3 also clearly shows the stacking, i.e. the good connection of the particles to one another, after sintering with the aid of the shell materials, which are relatively freely selectable, in combination with the core materials desired in each case, in order to achieve the optimal properties of the inlet coating for the respective application.
  • a covering as shown in FIG. 4, can be formed in layers by stacking particles 3 of the composite material together, the structure being determined by the sintering conditions can be influenced in the desired manner.
  • FIG. 4 it is shown that a single layer of coated balls is sintered onto a film 4 as a carrier, in particular a 0.2 mm thick Hastalloy metal film, and this forms a tape that is easy to glue or solder.
  • the total thickness of the covering was about 1 mm and above. It is practically unlimited.
  • FIG. 5 shows a multi-layer composite material, the outermost layer of which consists of very finely divided ( ⁇ 50 ⁇ m ”) powder and serves as a cover or barrier layer towards the housing.
  • a layer of powder is then placed underneath, made of hollow balls 3a, in particular with ceramic or glass-containing or metal-ceramic or metallic glass core and underneath a layer of nickel-coated graphite spheres ( ⁇ 200 ⁇ m ⁇ ) 3b.
  • the individual layers can be sintered one after the other or together as described above follow dense and / or smooth surface.
  • this layered composite material results in a tape with a film carrier 4, in particular for higher temperatures of approximately 550 ° C., in a thickness of the individual layers which can be selected depending on the application, preferably in the above. Area.
  • the hardness in Rockwell of the sintered coating varies from about + 10 to - 40 HSR 15 Y and below, compared to + 20 to + 60 HSR 15 Y with a known flame-sprayed coating.
  • FIG. 6 shows an embodiment of a covering in which a honeycomb-like carrier 6 is used instead of a conventional film, the honeycombs of which are advantageously filled with coated powder particles 5.
  • the invention is not limited to the use of specificallyhrie- surrounded materials for the particles of the composite material, nor to any particular particle shape, or a method of their preparation, as is the Aufbringart of the pad depending on the application, ie depending on the S trömungs- machine selectable instead of Gluing, soldering, welding can also be carried out using a diffusion or plating process, a pressing-on, shrink -on process, casting or the like.
  • the envelope materials can also be selected within wide limits.
  • the particles have on the one hand easily connected, with a dense and smooth surface (for example by sintering, or sintering and pressing), on the other se its can be quantitative it and delimit volume excessive proportion and thus any adverse or unwanted side effects.
  • the invention is advantageously applicable for run-in coatings and / or seals for both compressor and turbo b n i ne of turbomachines, such as gas turbines, whether it is axial or radial flow machines.
  • EB energy beam
  • laser ion

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)
  • Powder Metallurgy (AREA)
EP85106255A 1984-07-05 1985-05-22 Couche de rodage d'une turbomachine Expired EP0166940B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843424661 DE3424661A1 (de) 1984-07-05 1984-07-05 Einlaufbelag einer stroemungsmaschine
DE3424661 1984-07-05

Publications (3)

Publication Number Publication Date
EP0166940A2 true EP0166940A2 (fr) 1986-01-08
EP0166940A3 EP0166940A3 (en) 1986-05-21
EP0166940B1 EP0166940B1 (fr) 1989-03-29

Family

ID=6239843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85106255A Expired EP0166940B1 (fr) 1984-07-05 1985-05-22 Couche de rodage d'une turbomachine

Country Status (3)

Country Link
EP (1) EP0166940B1 (fr)
JP (1) JPS6123805A (fr)
DE (1) DE3424661A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU583516B2 (en) * 1984-06-25 1989-05-04 United Technologies Corporation Abrasive surfaced article for high temperature service
WO1993006341A1 (fr) * 1991-09-18 1993-04-01 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Garniture de rodage pour une turbomachine et procede pour sa fabrication
EP0555896A1 (fr) * 1992-02-12 1993-08-18 General Motors Corporation Procédé pour la fabrication d'une combination avec de configuration de moyen pour la production de lame ou component de turbine à gaz
WO2007112727A2 (fr) * 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles
DE102007019476A1 (de) 2007-04-25 2008-11-06 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Anstreifbelags
US8419359B2 (en) 2007-06-11 2013-04-16 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing a plastic compressor housing
CN105556001A (zh) * 2013-09-20 2016-05-04 Hrl实验室有限责任公司 具有低热容量和低热导率的热阻挡材料和涂层

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10221114C1 (de) * 2002-05-03 2003-09-11 Glatt Systemtechnik Gmbh Dichtung für Strömungsmaschinen
DE102006009054B4 (de) 2006-02-27 2007-11-22 Woco Industrietechnik Gmbh Gehäuse für Radialverdichter
DE102007009781B4 (de) 2007-02-27 2009-09-17 Woco Industrietechnik Gmbh Kunststoffverdichtergehäuse sowie Verfahren zu dessen Herstellung
DE102009009389B4 (de) 2009-02-18 2011-03-24 Woco Industrietechnik Gmbh Verdichtergehäuse, Verdichter umfassend ein solches Verdichtergehäuse und Verfahren zur Herstellung eines Verdichtergehäuses
DE102009016803A1 (de) * 2009-04-09 2010-10-14 Rolls-Royce Deutschland Ltd & Co Kg Labyrinth-Anstreifdichtung für eine Strömungsmaschine
DE102009018801A1 (de) 2009-04-24 2009-11-05 Daimler Ag Turbolader-Anordnung
FR3058457B1 (fr) * 2016-11-10 2018-12-07 Safran Helicopter Engines Procede de fabrication d'une pale de turbomachine.

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1089613B (de) * 1956-04-23 1960-09-22 Siemens Ag Verfahren zum Loetbarmachen von Werkstoffen durch fest haftende Schichten von Metall aus der Eisen-Nickel-Kobalt-Gruppe
US3594216A (en) * 1969-06-19 1971-07-20 Westinghouse Electric Corp Vapor phase deposition of metal from a metal-organic beta-ketoamine chelate
DE2239840A1 (de) * 1971-11-15 1973-05-24 United Aircraft Corp Schleifbares material fuer hohe temperaturen
DE2421504A1 (de) * 1973-05-04 1974-11-21 Ishizuka Glass Gesinterte metallische zusammensetzung
US3879830A (en) * 1971-06-30 1975-04-29 Gte Sylvania Inc Cathode for electron discharge device having highly adherent emissive coating of nickel and nickel coated carbonates
US3975165A (en) * 1973-12-26 1976-08-17 Union Carbide Corporation Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said
GB1465638A (en) * 1973-06-29 1977-02-23 Bbc Brown Boveri & Cie Method and means for reducing the clearance between a rotating member and a stationary member
FR2439053A1 (fr) * 1978-10-16 1980-05-16 Nippon Mining Co Procede de production d'une poudre composite a revetement multicouche
US4251272A (en) * 1978-12-26 1981-02-17 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US4291089A (en) * 1979-11-06 1981-09-22 Sherritt Gordon Mines Limited Composite powders sprayable to form abradable seal coatings
EP0067746A1 (fr) * 1981-06-12 1982-12-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Joint susceptible d'être usé par abrasion et son procédé de réalisation

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA901892A (en) * 1970-03-20 1972-06-06 A. W. Fustukian David Method of preparing metal alloy coated composite powders
FR2401310A1 (fr) * 1977-08-26 1979-03-23 Snecma Carter de turbine de moteur a reaction
DE3019920C2 (de) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1089613B (de) * 1956-04-23 1960-09-22 Siemens Ag Verfahren zum Loetbarmachen von Werkstoffen durch fest haftende Schichten von Metall aus der Eisen-Nickel-Kobalt-Gruppe
US3594216A (en) * 1969-06-19 1971-07-20 Westinghouse Electric Corp Vapor phase deposition of metal from a metal-organic beta-ketoamine chelate
US3879830A (en) * 1971-06-30 1975-04-29 Gte Sylvania Inc Cathode for electron discharge device having highly adherent emissive coating of nickel and nickel coated carbonates
DE2239840A1 (de) * 1971-11-15 1973-05-24 United Aircraft Corp Schleifbares material fuer hohe temperaturen
DE2421504A1 (de) * 1973-05-04 1974-11-21 Ishizuka Glass Gesinterte metallische zusammensetzung
GB1465638A (en) * 1973-06-29 1977-02-23 Bbc Brown Boveri & Cie Method and means for reducing the clearance between a rotating member and a stationary member
US3975165A (en) * 1973-12-26 1976-08-17 Union Carbide Corporation Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said
FR2439053A1 (fr) * 1978-10-16 1980-05-16 Nippon Mining Co Procede de production d'une poudre composite a revetement multicouche
US4251272A (en) * 1978-12-26 1981-02-17 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US4291089A (en) * 1979-11-06 1981-09-22 Sherritt Gordon Mines Limited Composite powders sprayable to form abradable seal coatings
EP0067746A1 (fr) * 1981-06-12 1982-12-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Joint susceptible d'être usé par abrasion et son procédé de réalisation

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU583516B2 (en) * 1984-06-25 1989-05-04 United Technologies Corporation Abrasive surfaced article for high temperature service
WO1993006341A1 (fr) * 1991-09-18 1993-04-01 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Garniture de rodage pour une turbomachine et procede pour sa fabrication
US5326647A (en) * 1991-09-18 1994-07-05 Mtu Motoren- Und Turbinen-Union Abradable layer for a turbo-engine and a manufacturing process
EP0555896A1 (fr) * 1992-02-12 1993-08-18 General Motors Corporation Procédé pour la fabrication d'une combination avec de configuration de moyen pour la production de lame ou component de turbine à gaz
US5250136A (en) * 1992-02-12 1993-10-05 General Motors Corporation Method of making a core/pattern combination for producing a gas-turbine blade or component
WO2007112727A3 (fr) * 2006-04-06 2007-12-21 Mtu Aero Engines Gmbh Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles
WO2007112727A2 (fr) * 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Procédé de fabrication d'une garniture d'étanchéité en nid d'abeilles
DE102007019476A1 (de) 2007-04-25 2008-11-06 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Anstreifbelags
WO2008131718A2 (fr) * 2007-04-25 2008-11-06 Mtu Aero Engines Gmbh Procédé de production d'un revêtement d'usure
WO2008131718A3 (fr) * 2007-04-25 2009-04-30 Mtu Aero Engines Gmbh Procédé de production d'un revêtement d'usure
US20100119706A1 (en) * 2007-04-25 2010-05-13 Mtu Aero Engines Gmbh Method for the production of an abradable coating
US8419359B2 (en) 2007-06-11 2013-04-16 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing a plastic compressor housing
CN105556001A (zh) * 2013-09-20 2016-05-04 Hrl实验室有限责任公司 具有低热容量和低热导率的热阻挡材料和涂层
EP3047047A4 (fr) * 2013-09-20 2017-05-24 Hrl Laboratories, Llc Matériaux et revêtements de barrière thermique présentant une faible capacité thermique et une faible conductivité thermique
CN105556001B (zh) * 2013-09-20 2017-10-27 Hrl实验室有限责任公司 具有低热容量和低热导率的热阻挡材料和涂层

Also Published As

Publication number Publication date
JPH0379523B2 (fr) 1991-12-19
DE3424661A1 (de) 1986-01-16
EP0166940A3 (en) 1986-05-21
EP0166940B1 (fr) 1989-03-29
JPS6123805A (ja) 1986-02-01
DE3424661C2 (fr) 1988-02-18

Similar Documents

Publication Publication Date Title
DE3015867C2 (fr)
DE2637443C2 (fr)
DE3018620C2 (de) Wärmedämmende und dichtende Auskleidung für eine thermische Turbomaschine
EP0166940A2 (fr) Couche de rodage d'une turbomachine
US4094673A (en) Abradable seal material and composition thereof
DE3785427T2 (de) Verschleissfeste siliziumkarbidpulver mit mehrschichtauflage.
EP0270670B1 (fr) Couche de metal antifriction et procede pour sa fabrication
DE4439950C2 (de) Metallisches Bauteil mit einer Verbundbeschichtung, Verwendung, sowie Verfahren zur Herstellung von metallischen Bauteilen
US5780116A (en) Method for producing an abradable seal
DE69613584T2 (de) Verfahren zum auftragen metallischer verbundschichten
US4139376A (en) Abradable seal material and composition thereof
DE68923921T2 (de) Kolben.
DE3103129A1 (de) Thermisch belastbares maschinenteil und verfahren zu dessen herstellung
US5162157A (en) Sliding material and method of manufacturing the same
GB2242240A (en) Bearings
EP0132667A1 (fr) Aube de turbine refroidie soumise à une charge thermique élevée
EP0484115A1 (fr) Extrémité abrasive pour aube de turbine
EP3252277A1 (fr) Bande de frottement abradable de joint externe
EP0170763B1 (fr) Revêtement protecteur contre l'usure
CH704833A1 (de) Komponente für eine Turbomaschine und ein Verfahren zum Herstellen einer derartigen Komponente.
DE2853724B2 (fr)
DE2208070C2 (de) Verbundkörper und Verfahren zu dessen Herstellung
EP0840809B1 (fr) Produit avec un corps de base metallique pourvu de canaux de refroidissement et sa fabrication
DE3916412A1 (de) Ueberzogene fasern zur verwendung in einer metallmatrix und in einem verbundkoerper
JPH06192774A (ja) 高強度裏金を有する銅合金すべり軸受及びその製造方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): DE FR GB IT SE

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

EL Fr: translation of claims filed
AK Designated contracting states

Kind code of ref document: A3

Designated state(s): DE FR GB IT SE

17P Request for examination filed

Effective date: 19860710

17Q First examination report despatched

Effective date: 19870423

ITF It: translation for a ep patent filed
GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): FR GB IT SE

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
ITTA It: last paid annual fee
EAL Se: european patent in force in sweden

Ref document number: 85106255.4

REG Reference to a national code

Ref country code: GB

Ref legal event code: 746

Effective date: 19960430

REG Reference to a national code

Ref country code: FR

Ref legal event code: D9

Free format text: CORRECTION

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19970410

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19970411

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19970423

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19980522

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19980523

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 19980531

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19980522

EUG Se: european patent has lapsed

Ref document number: 85106255.4

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST