EP1948839A2 - Verfahren zum herstellen eines einlaufbelags - Google Patents
Verfahren zum herstellen eines einlaufbelagsInfo
- Publication number
- EP1948839A2 EP1948839A2 EP06805507A EP06805507A EP1948839A2 EP 1948839 A2 EP1948839 A2 EP 1948839A2 EP 06805507 A EP06805507 A EP 06805507A EP 06805507 A EP06805507 A EP 06805507A EP 1948839 A2 EP1948839 A2 EP 1948839A2
- Authority
- EP
- European Patent Office
- 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.)
- Withdrawn
Links
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-side component of a turbomachine.
- Turbomachines such as gas turbines, typically include a plurality of rotating blades and a plurality of stationary vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a stationary housing.
- sealing systems Particularly problematic in turbomachinery compliance with a minimum gap between the rotating blades and the fixed housing of a high pressure compressor. Namely, the highest absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing. This is partly due to the fact that in compressor blades on shrouds, as used in turbine blades, is dispensed with.
- the inlet lining disclosed therein has as its first component a metallic, oxidation-resistant matrix phase of an MCrAlY material, as a second component via an intermetallic phase of preferably ⁇ -NiAL and as a third component via pores produced by burning out polyester or polyimide.
- the inlet covering disclosed in US Pat. No. 6,660,405 B2 comprises ceramic particles as the fourth component, such as, for example, particles of hexagonal boron nitride.
- the present invention is based on the problem to provide a novel method for producing an inlet lining.
- the method according to the invention comprises at least the following steps: a) provision of a stator-side component of a turbomachine to be provided with an inlet lining; b) providing a mixture of a solvent, solvent-insoluble particles of a metallic base material for the lead deposit and a filler, the filler having at least one solvent-soluble component; c) applying the mixture to the stator-side component; d) drying the stator-side component and the mixture applied to the component while at least partially expelling the solvent to provide a porous green body in the area of the applied and dried mixture; e) diffusion heat treatment of the component for the diffusion of aluminum and / or chromium and for the formation of intermetallic phases in the forming inlet lining.
- the intermetallic phase thereof is provided by diffusing aluminum and / or chromium into the inlet lining of the component via diffusion heat treatment.
- the intermetallic phase of the inlet lining is provided by means of diffusion heat treatment.
- a solvent-insoluble additive is further introduced into the mixture in step b), wherein the additive is decomposed or burned out in the diffusion heat treatment in order to form a macroporosity in the inlet lining that forms.
- insoluble ceramic particles can be introduced into the mixture in the solvent.
- the present invention relates to a method for producing an inlet lining on a stator-side component of a turbomachine, in particular on a component of a housing of a gas turbine aircraft engine.
- the inventive method is divided into five main steps.
- a stator-side to be provided with an inlet lining component of a turbomachine is provided.
- a mixture is provided wherein the mixture is formed of at least one of a solvent, solvent insoluble particles of a metallic base material for the inlet coating, and a filler having at least one solvent soluble component.
- the mixture is applied to the statorseltige component, in the section in which the inlet lining is to be provided.
- a fourth main step the stator-side component and the mixture applied to the component are dried, during which drying the solvent is expelled at least partially from the applied mixture to form a porous green body formed in the region of the applied mixture.
- aluminum and / or chromium is diffused in a fifth main step of the process according to the invention by means of a diffusion heat treatment so as to provide an intermetallic phase in the inlet lining that forms.
- a mixture is provided which comprises at least one solvent, solvent-insoluble particles of the metallic base material for the inlet lining and the filler having at least one solvent-soluble component ,
- the solvent is in particular water.
- the insoluble in the solvent particles for the metallic base material of the inlet lining are preferably powdered MCrAlY particles.
- the filler is in particular polyvinyl alcohol or methyl cellulose esters.
- a solvent-insoluble additive may further be added to the mixture, and the additive is decomposed in the fifth main step of the process of the invention in the diffusion heat treatment.
- This additive is preferably a polymer such as polyester or polyimide, which forms a macroporosity after burnout in the inlet lining. It should be noted that porosity is already provided in the inlet lining when the solvent evaporates, but these are smaller pores and therefore a microporosity.
- ceramic particles are introduced into the mixture in the second main step of the method according to the invention in the provision of the mixture.
- the ceramic particles may be particles of hexagonal boron nitride, graphite or clay mineral.
- CaO particles or MgO particles can be used as ceramic particles.
- NiC particles when NiC particles are used as the base material for the inlet lining in the mixture, ceramic particles of graphite are preferably admixed to the mixture.
- NiCrAl particles are used as base material for the inlet lining in the mixture, ceramic particles of clay mineral are introduced into the mixture.
- nickel base alloy particles or aluminum base alloy particles or cobalt base alloy particles are used as the base material for the inlet lining in the mixture, hexagonal boron nitride ceramic particles are introduced into the mixture.
- the mixture provided in the second main step is either a low-viscosity, slurry-like mixture or a viscous, pasty mixture.
- the mixture formed as a low-viscosity slip or viscous paste is applied by brushing or dipping or spraying onto the region of the stator-side component on which the inlet lining is to be formed.
- the mixture provided in the second main step can alternatively also be provided as a highly viscous, tape-like shaped body, which is then bonded in the third main step of the method according to the invention to the region of the stator-side component on which the inlet lining is to be formed.
- the drying of the stator-side component and the applied mixture at a temperature of at most 100 ° C, wherein the drying is preferably carried out at room temperature.
- the solvent is expelled at least partially from the mixture, so that in the area of the applied and dried mixture, a porous, namely microporous, green body is formed.
- the solvent-soluble component of the filler serves as a binder for the green body.
- the diffusion heat treatment in the sense of diffusion annealing takes place in order to form an intermetallic phase in the inlet lining by diffusion of aluminum and / or chromium.
- an intermetallic phase of ⁇ -NiAl is preferably formed. Accordingly, this intermetallic phase is produced by the heat diffusion treatment and is therefore only partially in stoichiometric form.
- the inlet lining thus provided has a metallic phase of preferably a MCrAlY material, wherein this metallic phase provides the basic structure of the inlet lining and serves the connection to the stator-side component. Furthermore, the inlet lining has an intermetallic phase, which serves to give the material at the junctions of individual particles in the inlet lining a brittle character, whereby the running ability of the inlet lining is improved.
- the intermetallic phase increases the oxidation resistance of the inlet lining.
- the porosity of the inlet lining further optimizes its ability to run-in.
Landscapes
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- General Chemical & Material Sciences (AREA)
- Nanotechnology (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
---|---|
EP1948839A2 true EP1948839A2 (de) | 2008-07-30 |
Family
ID=37690153
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06805507A Withdrawn EP1948839A2 (de) | 2005-11-19 | 2006-11-10 | Verfahren zum herstellen eines einlaufbelags |
Country Status (4)
Country | Link |
---|---|
US (2) | US20090202379A1 (de) |
EP (1) | EP1948839A2 (de) |
DE (1) | DE102005055200A1 (de) |
WO (1) | WO2007056979A2 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
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 |
DE102009051554A1 (de) * | 2009-10-31 | 2011-05-05 | Mtu Aero Engines Gmbh | Verfahren zum Erzeugen eines Einlaufbelags an einer Strömungsmaschine |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3649226A (en) * | 1969-04-01 | 1972-03-14 | Gen Motors Corp | Oxidation-sulfidation resistant articles |
FR2119920B1 (de) * | 1970-12-29 | 1975-07-18 | United Aircraft Corp | |
US4251272A (en) * | 1978-12-26 | 1981-02-17 | Union Carbide Corporation | Oxidation resistant porous abradable seal member for high temperature service |
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 |
US7101448B2 (en) * | 1998-06-20 | 2006-09-05 | Mtu Aero Engines Gmbh | Process for producing a cladding for a metallic component |
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 |
US6660405B2 (en) * | 2001-05-24 | 2003-12-09 | General Electric Co. | High temperature abradable coating for turbine shrouds without bucket tipping |
US6547522B2 (en) * | 2001-06-18 | 2003-04-15 | General Electric Company | Spring-backed abradable seal for turbomachinery |
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 |
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 |
US7390534B2 (en) * | 2003-10-31 | 2008-06-24 | General Electric Company | Diffusion coating process |
US7332024B2 (en) * | 2004-04-29 | 2008-02-19 | General Electric Company | Aluminizing composition and method for application within internal passages |
-
2005
- 2005-11-19 DE DE102005055200A patent/DE102005055200A1/de not_active Ceased
-
2006
- 2006-11-10 US US12/093,395 patent/US20090202379A1/en not_active Abandoned
- 2006-11-10 EP EP06805507A patent/EP1948839A2/de not_active Withdrawn
- 2006-11-10 WO PCT/DE2006/001973 patent/WO2007056979A2/de active Application Filing
-
2011
- 2011-11-18 US US13/300,385 patent/US20120128875A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO2007056979A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2007056979A2 (de) | 2007-05-24 |
WO2007056979A3 (de) | 2008-05-15 |
US20120128875A1 (en) | 2012-05-24 |
DE102005055200A1 (de) | 2007-05-24 |
US20090202379A1 (en) | 2009-08-13 |
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Legal Events
Date | Code | Title | Description |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
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Effective date: 20080530 |
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Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
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AX | Request for extension of the european patent |
Extension state: AL BA HR MK RS |
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R17D | Deferred search report published (corrected) |
Effective date: 20080515 |
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17Q | First examination report despatched |
Effective date: 20091208 |
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DAX | Request for extension of the european patent (deleted) | ||
RBV | Designated contracting states (corrected) |
Designated state(s): DE ES FR GB IT |
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RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: MTU AERO ENGINES AG |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20170601 |