EP0166940B1 - Einlaufbelag einer Strömungsmaschine - Google Patents

Einlaufbelag einer Strömungsmaschine Download PDF

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Publication number
EP0166940B1
EP0166940B1 EP85106255A EP85106255A EP0166940B1 EP 0166940 B1 EP0166940 B1 EP 0166940B1 EP 85106255 A EP85106255 A EP 85106255A EP 85106255 A EP85106255 A EP 85106255A EP 0166940 B1 EP0166940 B1 EP 0166940B1
Authority
EP
European Patent Office
Prior art keywords
coating
running
sintered
nickel
turbomachine
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
Application number
EP85106255A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0166940A2 (de
EP0166940A3 (en
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 GmbH
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/de
Publication of EP0166940A3 publication Critical patent/EP0166940A3/de
Application granted granted Critical
Publication of EP0166940B1 publication Critical patent/EP0166940B1/de
Expired 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
    • 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 invention relates to a sintered inlet lining for a turbomachine, in particular a gas turbine, to reduce the radial gap between rotor blades and housing, with spherical particles which have a graphite core and a thin-walled shell made of nickel or a nickel alloy with chromium, aluminum or copper.
  • a porous inlet lining for a turbomachine which serves to reduce the radial gap between the rotor blades and the housing.
  • This coating consists of a sintered powder mixture with essentially three parts, of which a first part is a Ni-Cr alloy powder, a second part is a CoAIY alloy powder and a third part is a powder consisting of spherical particles.
  • the spherical particles have a graphite core and a shell made of Ni, Fe, Co, Cr or their alloys. Due to the porosity of the coating and the large proportion of metallic particles, there is a risk that downstream components will be endangered by erosion of the coating or that gaps or small cooling bores will become clogged.
  • an inlet coating which is formed by flame spraying powder, the powder particles having a core made of non-metallic material with good sliding properties and a shell made of nickel or nickel alloy.
  • a covering produced in this way is also porous.
  • a sintered material which consists of particles with a glass-ceramic core and a metallic shell surrounding them. Due to its hardness and abrasion resistance, such a material is suitable for brake pads, electrical contacts and collectors; it would not be suitable for an enema.
  • the object of the invention is to provide a relatively soft inlet lining, which allows the radial gap between the rotor blades and the housing of a turbomachine to be minimized and at the same time has low sensitivity to temperature and erosion.
  • the inlet coating consists exclusively of spherical particles which are sintered to form a layer with a more dense, closed surface.
  • a major advantage of the invention is that the spherical particles, since their shells are made of metal, are easy to connect and to compress.
  • a further advantage is that the core and shell formation of the particles mean that the overall metallic content of the composite material can be kept lower than in the case of known inlet linings, which has the harmful effect of abraded material in the turbine (e.g. clogging of cooling air bores, subsequent erosion) Turbine levels, environmental pollution) reduced.
  • a further advantage of the inlet lining according to the invention is that low blade tip wear on the rotor can be achieved with low temperature sensitivity at the same time.
  • FIG. 1 shows a spherical particle with a graphite core and a metallic shell 2 made of nickel or a nickel alloy.
  • Nickel or a nickel alloy is used as the cladding material because the operating temperature is very high without damaging oxidation (in the range of around 500 °).
  • a graphite core is used because of the good sliding properties. 1 can have a diameter between about 50 and 150 11m. The hardness of the covering produced in the sintering process depends mainly on the size and amount of the graphite of the core as well as the shell material used and its amount or thickness. If a high temperature resistance of the inlet lining is required, the nickel can be alloyed with a higher alloy. If the operating temperatures are low, nickel can be alloyed electrolytically with aluminum or with copper, or as the shell material.
  • 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, but only about 1/3 by weight.
  • the particles are advantageously sintered in a vacuum oven at a low pressure of __ ⁇ 10- 1 M Pa and a temperature of 1000 ° C to about 1500 ° C and a time of a few hours.
  • the metallic shell material in its alloy is preferred to be selected according to the fact that it can be easily peeled off from a compressor or turbine blade of an engine. It must be taken into account here that most of the known blade materials lose their hardness at high temperatures, ie when the blade tips are brushed against.
  • the running-in covering can still be compacted by rolling or rolling.
  • FIG. 2 shows a micrograph through a sintered inlet coating made of composite material.
  • the intimate connection of the particles to one another means that erosion caused, for example, by aggressive gas from a gas turbine is not possible.
  • Fig. 2 shows that the pure spherical shape is essentially only in the starting material (powder). Any grain shape can be present after sintering.
  • Fig. 2 also clearly shows the stacking d. H. the good connection of the particles to one another after sintering with the help of the coating materials.
  • a covering can be formed in layers by stacking particles 3 of the composite material together, the microstructure being able to be influenced in a desired manner by the sintering conditions.
  • Fig. 3 shows a on a film 4 as a carrier, for. B. a 0.2 mm thick metal foil, sintered layer that forms a well-adhesive or solderable tape.

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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
  • Powder Metallurgy (AREA)
EP85106255A 1984-07-05 1985-05-22 Einlaufbelag einer Strömungsmaschine Expired EP0166940B1 (de)

Applications Claiming Priority (2)

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

Publications (3)

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

Family

ID=6239843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85106255A Expired EP0166940B1 (de) 1984-07-05 1985-05-22 Einlaufbelag einer Strömungsmaschine

Country Status (3)

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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4130946C1 (ja) * 1991-09-18 1992-09-03 Mtu Muenchen Gmbh
US7862298B2 (en) 2006-02-27 2011-01-04 Woco Industrietechnik Gmbh Centrifugal compressor housing
US8342800B2 (en) 2007-02-27 2013-01-01 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing same
CN109937103A (zh) * 2016-11-10 2019-06-25 赛峰直升机发动机公司 用于制造涡轮机叶片的方法

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL75564A (en) * 1984-06-25 1988-02-29 United Technologies Corp Abrasive surfaced article for high temperature service
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
DE10221114C1 (de) * 2002-05-03 2003-09-11 Glatt Systemtechnik Gmbh Dichtung für Strömungsmaschinen
DE102006016147A1 (de) * 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Wabendichtung
DE102007019476A1 (de) * 2007-04-25 2008-11-06 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Anstreifbelags
DE102007027282B3 (de) 2007-06-11 2008-11-13 Woco Industrietechnik Gmbh Kunststoffverdichtergehäuse und Verfahren zur Herstellung eines Kunststoffverdichtergehäuses
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
US9719176B2 (en) * 2013-09-20 2017-08-01 Hrl Laboratories, Llc Thermal barrier materials and coatings with low heat capacity and low thermal conductivity

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2239840A1 (de) * 1971-11-15 1973-05-24 United Aircraft Corp Schleifbares material fuer hohe temperaturen

Family Cites Families (12)

* 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
CA901892A (en) * 1970-03-20 1972-06-06 A. W. Fustukian David Method of preparing metal alloy coated composite powders
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
CH589221A5 (ja) * 1973-06-29 1977-06-30 Bbc Brown Boveri & Cie
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
FR2401310A1 (fr) * 1977-08-26 1979-03-23 Snecma Carter de turbine de moteur a reaction
JPS5553017A (en) * 1978-10-16 1980-04-18 Nippon Mining Co Method of manufacturing multiple coating composite powder
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
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
FR2507729B1 (fr) * 1981-06-12 1986-08-22 Snecma Joint susceptible d'etre use par abrasion et son procede de realisation

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2239840A1 (de) * 1971-11-15 1973-05-24 United Aircraft Corp Schleifbares material fuer hohe temperaturen

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4130946C1 (ja) * 1991-09-18 1992-09-03 Mtu Muenchen Gmbh
US7862298B2 (en) 2006-02-27 2011-01-04 Woco Industrietechnik Gmbh Centrifugal compressor housing
US8342800B2 (en) 2007-02-27 2013-01-01 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing same
CN109937103A (zh) * 2016-11-10 2019-06-25 赛峰直升机发动机公司 用于制造涡轮机叶片的方法
CN109937103B (zh) * 2016-11-10 2022-02-25 赛峰直升机发动机公司 用于制造涡轮机叶片的方法

Also Published As

Publication number Publication date
EP0166940A2 (de) 1986-01-08
DE3424661A1 (de) 1986-01-16
JPH0379523B2 (ja) 1991-12-19
DE3424661C2 (ja) 1988-02-18
JPS6123805A (ja) 1986-02-01
EP0166940A3 (en) 1986-05-21

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