US20090202379A1 - Method for producing an inlet lining - Google Patents

Method for producing an inlet lining Download PDF

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Publication number
US20090202379A1
US20090202379A1 US12/093,395 US9339506A US2009202379A1 US 20090202379 A1 US20090202379 A1 US 20090202379A1 US 9339506 A US9339506 A US 9339506A US 2009202379 A1 US2009202379 A1 US 2009202379A1
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US
United States
Prior art keywords
mixture
component
inlet lining
solvent
particles
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.)
Abandoned
Application number
US12/093,395
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English (en)
Inventor
Andre Werner
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
Individual
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 Individual filed Critical Individual
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WERNER, ANDRE
Publication of US20090202379A1 publication Critical patent/US20090202379A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • C23C10/18—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
    • 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
    • C23C10/18—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
    • C23C10/26—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions more than one element being diffused
    • 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
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • 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
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/1204—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material inorganic material, e.g. non-oxide and non-metallic such as sulfides, nitrides based compounds
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/125—Process of deposition of the inorganic material
    • C23C18/1262—Process of deposition of the inorganic material involving particles, e.g. carbon nanotubes [CNT], flakes
    • C23C18/127—Preformed particles
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/12—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material
    • C23C18/125—Process of deposition of the inorganic material
    • C23C18/1295—Process of deposition of the inorganic material with after-treatment of the deposited inorganic material

Definitions

  • the invention relates to a method for producing an inlet lining on a stator-sided component of a turbine engine.
  • Turbine engines such as gas turbines, usually comprise a plurality of rotating rotor blades and a plurality of stationary guide vanes.
  • the rotating rotor blades rotate together with a rotor; and the rotating rotor blades and the guide vanes are enclosed by a stationary housing.
  • This also includes the so-called sealing systems.
  • maintaining a minimum gap between the rotating rotor blades and the stationary housing of a high pressure compressor poses a special problem.
  • high pressure compressors experience the highest absolute temperatures and temperature gradients, a feature that renders the maintenance of a gap of the rotating rotor blades in relation to the stationary housing difficult. The reason lies, inter alia, in the fact that compressor rotor blades dispense with shrouds, as used in the case of turbine rotor blades.
  • rotor blades in compressors do not exhibit a shroud. Therefore, upon so-called rubbing against the stationary housing, the ends or rather the tips of the rotor blades are exposed to a direct friction contact with the housing. This type of rubbing of the tips of the rotor blades against the housing is induced by the manufacturing tolerances when setting a minimum radial gap. Since the friction contact causes the tips of the rotor blades to be abraded at the same material, an undesired increase in the gap may occur over the entire periphery of the housing and the rotor. In order to avoid this increase, the ends or rather the tips of the rotor blades are armored with a hard lining or with abrasive particles, as already known from the state of the art.
  • U.S. Pat. No. 6,660,405 B2 discloses an inlet lining, which is intended for gas turbine components and is made of three components.
  • the disclosed inlet lining exhibits, as a first component, a metallic, oxidation-resistant matrix phase comprising an MCrAlY material, where M is a metal, for example, iron, chromium, nickel or cobalt, Cr is chromium, Al is aluminum and Y is yttrium; as the second component, an intermetallic phase comprising preferably ⁇ -NiAl (beta nickel aluminum); and, as the third component, pores, created by burning off polyester or polyimide.
  • the inlet lining, disclosed in U.S. Pat. No. 6,660,405 B2 may or may not comprise, as the fourth component, ceramic particles, such as particles composed of hexagonal boron nitride.
  • this type of inlet lining is manufactured by producing a mixture comprising the metallic MCrAlY material, the intermetallic ⁇ -NiAl material and polyester or polyimide. Then this mixture is applied by thermal spraying to the component to be provided with the inlet lining. According to this state of the art, an intermetallic ⁇ -NiAl material is used directly in the production of the mixture to be applied to the component.
  • the present invention is based on the problem of providing a novel method for producing an inlet lining.
  • the inventive method comprises at least the following steps: a) providing a stator-sided component of a turbine engine, this component being provided with an inlet lining; b) providing a mixture consisting of a solvent; particles of a metallic parent material for the inlet lining, said particles being insoluble in the solvent; and a filler, this filler having at least one constituent that is soluble in the solvent; c) applying the mixture to the stator-sided component; d) drying the stator-sided component and the mixture, applied to the component, while at least partially expelling the solvent in order to provide a porous green body in the area of the applied and dried mixture; e) diffusion heat treating the component for inwardly diffusing aluminum and/or chromium and for forming the intermetallic phases in the resulting inlet lining.
  • the intermetallic phase of this inlet lining is provided by inwardly diffusing the aluminum and/or chromium into the inlet lining of the component by means of diffusion heat treatment. Therefore, during the production of the mixture the present invention, described here, does not use an intermetallic material, but rather the intermetallic phase of the inlet lining is provided by way of a diffusion heat treatment.
  • an advantageous further development of the invention provides that in step b) an additional substance, which is insoluble in the solvent, is introduced into the mixture.
  • the additional substance is decomposed and/or burned off during the diffusion heat treatment in order to create a macro-porosity in the inlet lining that forms.
  • ceramic particles, which are insoluble in the solvent may be introduced into the mixture.
  • the present invention relates to a method for producing an inlet lining on a stator-sided component of a turbine engine, in particular on a component of a housing of a gas turbine aircraft engine.
  • the inventive method is subdivided into five main steps.
  • the first main step provides a stator-sided component of a turbine engine, said component being provided with an inlet lining.
  • a second main step provides a mixture, said mixture consisting of at least a solvent; particles of a metallic parent material for the inlet lining, said particles being insoluble in the solvent; and a filler, which exhibits at least one constituent that is soluble in the solvent.
  • the mixture is applied to the stator-sided component, and, in particular, in a section, in which the inlet lining is supposed to be provided.
  • the stator-sided component and the mixture, applied to the component are dried.
  • the solvent is expelled at least partially from the applied mixture while at the same time forming a porous green body, resulting in the area of the applied mixture.
  • aluminum and/or chromium is/are inwardly diffused by way of a diffusion heat treatment in order to provide in this way an intermetallic phase in the resulting inlet lining.
  • a mixture is provided, as stated above.
  • This mixture comprises at least one solvent; particles of the metallic parent material for the inlet lining, said particles being insoluble in the solvent; and the filler, which exhibits at least one constituent that is soluble in the solvent.
  • the solvent is, in particular, water.
  • the particles, which are insoluble in the solvent and which are intended for the metallic parent material of the inlet lining, are preferably powdery MCrAlY particles.
  • the filler is, in particular, polyvinyl alcohol or methyl cellulose ester.
  • an additional substance which is insoluble in the solvent, may be introduced into the mixture.
  • the additional substance is decomposed and/or burned off during the diffusion heat treatment in the fifth main step of the inventive method.
  • This additional substance is preferably a polymer, like polyester or polyimide, which upon burning off creates a macro-porosity in the inlet lining. It must be pointed out that the inlet lining is provided with a porosity as early as during the removal of the solvent by evaporation. In this case, however, the resulting pores are smaller; and, thus, the process involves a micro-porosity.
  • the ceramic particles may be particles composed of hexagonal boron nitride, graphite or clay mineral. Furthermore, CaO (calcium oxide) particles and/or MgO (magnesium oxide) particles may be used as the ceramic particles. Then, if NiC (nickel carbide) particles are used as the parent material for the inlet lining in the mixture, preferably ceramic particles composed of graphite are added to the mixture. Then, in contrast, if NiCrAl (nickel chromium aluminum) particles are used as the parent material for the inlet lining in the mixture, then ceramic particles composed of clay mineral are introduced into the mixture.
  • ceramic particles composed of hexagonal boron nitride may be introduced into the mixture.
  • the mixture which is provided in the second main step, is either a highly liquid, slip-like mixture or a viscous, pasty mixture.
  • the mixture produced as a highly liquid slip or viscous paste, is applied to the area of the stator-sided component, on which the inlet lining is to form, by brushing or immersion or spraying.
  • the mixture which is provided in the second main step of the inventive method, may also be provided as a highly viscous, tape-like molded article. Then in the third main step of the inventive method, this tape-like molded article is cemented on the area of the stator-sided component, on which the inlet lining is to be formed.
  • the drying of the stator-sided component and the applied mixture takes place at a maximum temperature of 100 deg. C. in the fourth main step.
  • the drying is carried out preferably at room temperature.
  • the solvent is expelled at least partially from the mixture, so that a porous-that is, micro-porous-green body is formed in the area of the applied and dried mixture.
  • the constituent of the filler said constituent being soluble in the solvent, serves as the binder for the green body.
  • the fifth main step of the inventive method provides a diffusion heat treatment in the sense of a diffusion annealing in order to create an intermetallic phase in the inlet lining through inwards diffusion of aluminum and/or chromium.
  • an intermetallic phase consisting of ⁇ -NiAl is preferably formed. Consequently this intermetallic phase is the result of the heat diffusion treatment and exists, therefore, only to some extent in stoichiometric form.
  • the inlet lining which is provided in this way, exhibits a metallic phase consisting preferably of a MCrAlY material.
  • the metallic phase provides the base structure of the inlet lining and serves to attach the stator-sided component.
  • the inlet lining exhibits an intermetallic phase, which serves to impart a brittle character to the material at the connecting points of the individual particles in the inlet lining, thus improving the inlet capacity of the inlet lining.
  • the intermetallic phase enhances the oxidation resistance of the inlet lining. Furthermore, the porosity of the inlet lining optimizes the inlet capacity of the same. Owing to the introduction of the ceramic particles, the detachment of the particles when the rotor blades rub against the inlet lining may be controlled.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Inorganic Chemistry (AREA)
  • Nanotechnology (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
US12/093,395 2005-11-19 2006-11-10 Method for producing an inlet lining Abandoned US20090202379A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102005055200.5 2005-11-19
DE102005055200A DE102005055200A1 (de) 2005-11-19 2005-11-19 Verfahren zum Herstellen eines Einlaufbelags
PCT/DE2006/001973 WO2007056979A2 (de) 2005-11-19 2006-11-10 Verfahren zum herstellen eines einlaufbelags

Publications (1)

Publication Number Publication Date
US20090202379A1 true US20090202379A1 (en) 2009-08-13

Family

ID=37690153

Family Applications (2)

Application Number Title Priority Date Filing Date
US12/093,395 Abandoned US20090202379A1 (en) 2005-11-19 2006-11-10 Method for producing an inlet lining
US13/300,385 Abandoned US20120128875A1 (en) 2005-11-19 2011-11-18 Method for Producing an Inlet Lining

Family Applications After (1)

Application Number Title Priority Date Filing Date
US13/300,385 Abandoned US20120128875A1 (en) 2005-11-19 2011-11-18 Method for Producing an Inlet Lining

Country Status (4)

Country Link
US (2) US20090202379A1 (de)
EP (1) EP1948839A2 (de)
DE (1) DE102005055200A1 (de)
WO (1) WO2007056979A2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070199727A1 (en) * 2006-02-27 2007-08-30 Woco Industrietechnik Gmbh Centrifugal compressor housing
US20080304960A1 (en) * 2007-06-11 2008-12-11 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing a plastic compressor housing
US20090053051A1 (en) * 2007-02-27 2009-02-26 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing same
US20120251310A1 (en) * 2009-10-31 2012-10-04 Mtu Aero Engines Gmbh Method for producing an abradable coating on a turbomachine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009009389B4 (de) 2009-02-18 2011-03-24 Woco Industrietechnik Gmbh Verdichtergehäuse, Verdichter umfassend ein solches Verdichtergehäuse und Verfahren zur Herstellung eines Verdichtergehäuses

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3649226A (en) * 1969-04-01 1972-03-14 Gen Motors Corp Oxidation-sulfidation resistant articles
US4251272A (en) * 1978-12-26 1981-02-17 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US20030054196A1 (en) * 2001-05-24 2003-03-20 Yuk-Chiu Lau High temperature abradable coating for turbine shrouds without bucket tipping
US20030111140A1 (en) * 1998-06-20 2003-06-19 Mtu Aero Engines Gmbh. Process for producing a cladding for a metallic component
US20040005452A1 (en) * 2002-01-14 2004-01-08 Dorfman Mitchell R. High temperature spray dried composite abradable powder for combustion spraying and abradable barrier coating produced using same
US20050095358A1 (en) * 2003-10-31 2005-05-05 General Electric Company Diffusion coating process

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2119920B1 (de) * 1970-12-29 1975-07-18 United Aircraft Corp
US5196471A (en) * 1990-11-19 1993-03-23 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
DE19827620C2 (de) * 1998-06-20 2003-12-18 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Panzerung für ein metallisches Bauteil und dessen Verwendung
US6413582B1 (en) * 1999-06-30 2002-07-02 General Electric Company Method for forming metallic-based coating
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
US6875464B2 (en) * 2003-04-22 2005-04-05 General Electric Company In-situ method and composition for repairing a thermal barrier coating
DE10347363A1 (de) * 2003-10-11 2005-05-12 Mtu Aero Engines Gmbh Verfahren zur lokalen Alitierung, Silizierung oder Chromierung von metallischen Bauteilen
US7332024B2 (en) * 2004-04-29 2008-02-19 General Electric Company Aluminizing composition and method for application within internal passages

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3649226A (en) * 1969-04-01 1972-03-14 Gen Motors Corp Oxidation-sulfidation resistant articles
US4251272A (en) * 1978-12-26 1981-02-17 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US20030111140A1 (en) * 1998-06-20 2003-06-19 Mtu Aero Engines Gmbh. Process for producing a cladding for a metallic component
US20030054196A1 (en) * 2001-05-24 2003-03-20 Yuk-Chiu Lau High temperature abradable coating for turbine shrouds without bucket tipping
US6660405B2 (en) * 2001-05-24 2003-12-09 General Electric Co. High temperature abradable coating for turbine shrouds without bucket tipping
US20040005452A1 (en) * 2002-01-14 2004-01-08 Dorfman Mitchell R. High temperature spray dried composite abradable powder for combustion spraying and abradable barrier coating produced using same
US20050095358A1 (en) * 2003-10-31 2005-05-05 General Electric Company Diffusion coating process

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070199727A1 (en) * 2006-02-27 2007-08-30 Woco Industrietechnik Gmbh Centrifugal compressor housing
US7862298B2 (en) 2006-02-27 2011-01-04 Woco Industrietechnik Gmbh Centrifugal compressor housing
US20090053051A1 (en) * 2007-02-27 2009-02-26 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing same
US8342800B2 (en) 2007-02-27 2013-01-01 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing same
US20080304960A1 (en) * 2007-06-11 2008-12-11 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing a plastic compressor housing
US8419359B2 (en) 2007-06-11 2013-04-16 Woco Industrietechnik Gmbh Plastic compressor housing and method for producing a plastic compressor housing
US20120251310A1 (en) * 2009-10-31 2012-10-04 Mtu Aero Engines Gmbh Method for producing an abradable coating on a turbomachine

Also Published As

Publication number Publication date
EP1948839A2 (de) 2008-07-30
WO2007056979A2 (de) 2007-05-24
WO2007056979A3 (de) 2008-05-15
US20120128875A1 (en) 2012-05-24
DE102005055200A1 (de) 2007-05-24

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