EP2035595A2 - Method of repairing intake coatings - Google Patents
Method of repairing intake coatingsInfo
- Publication number
- EP2035595A2 EP2035595A2 EP07764369A EP07764369A EP2035595A2 EP 2035595 A2 EP2035595 A2 EP 2035595A2 EP 07764369 A EP07764369 A EP 07764369A EP 07764369 A EP07764369 A EP 07764369A EP 2035595 A2 EP2035595 A2 EP 2035595A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- diffusion
- damaged
- donor layer
- inlet lining
- inlet
- 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- Withdrawn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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- 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
- C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
- C23C10/16—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases more than one element being diffused in more than 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
- 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
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0463—Cobalt
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/70—Application in combination with
- F05D2220/76—Application in combination with an electrical generator
- F05D2220/762—Application in combination with an electrical generator of the direct current (D.C.) type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/22—Manufacture essentially without removing material by sintering
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/40—Heat treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/11—Iron
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/224—Carbon, e.g. graphite
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/228—Nitrides
Definitions
- the present invention relates to a method for repairing run-in coverings, in particular run-in coverings for use in compressor and turbine components.
- Inlet linings are used in particular in so-called gap holding systems in the compressor and turbine components.
- the inlet coverings have the task to keep a sealing gap of rotating blading to a housing as well as the gap of a standing blading to the rotating rotor hub minimal and thus to guarantee a stable performance with high efficiency.
- the rotating components of the turbine have sealing fins, which run in a known manner against the inlet linings or seals.
- Such a honeycomb-shaped seal is disclosed by WO 2004/061340 Al.
- said inlet process can lead to damage of the inlet lining, to the effect that no uniform removal of the inlet lining or the seal takes place, but it comes to local damage in the form of irregularly shaped and relatively deep eruptions from the inlet lining.
- gap isolation between a rotor and a stator is an important factor in aircraft engines and gas turbines, which affects the efficiency and reliability of the system.
- Deterioration i. an increase in the gap between the rotor and the compressor housing, as caused for example by the said local damage, affects both the efficiency and the surge limit of the compressor with increasing operating time negative.
- a method for the repair of run-in coverings, in particular of run-in coverings for use in compressor and turbine components comprises the following method steps: a) filling a damaged point of the run-in covering with a material whose material composition corresponds or is comparable to that of the run-in covering or its material properties are comparable with the material properties of the inlet lining; b) drying the material filled in the damaged area; c) applying a diffusion donor layer over the area of the damaged site and to the filled material; and d) heat treatment of the inlet lining at least in the region of the damaged spot for local diffusion of at least one metallic element from the diffusion donor layer into the filled material.
- a repair method for inlet coverings is provided for the first time, which makes it possible to repair locally limited damage to the inlet lining. Since in such local damage not the entire inlet lining must be removed, the inventive method represents a simple and cost-effective solution for repairing damaged inlet linings. It is of essential importance that the inserted into the damaged site material of the material composition of the inlet lining corresponds or with this is comparable or whose material properties are at least comparable with the material properties of the inlet lining.
- the material used in the erf ⁇ ndungswashen method can be designed as a slip, paste or tape.
- the material consists of one provided with a binder metallic powder, wherein the metallic powder is made on a Ni, Co and / or Fe base.
- a binder for the material polyvinyl alcohol, polyvinyl acetate, cellulose esters and / or acrylic dispersions can be selected.
- the material contains ceramic constituents, such as, for example, graphite, hexagonal boron nitride and / or bentonite.
- the order of the diffusion donor layer according to method step c) can also be done on the areas adjacent to the damaged area areas of the inlet cover. As a result, an intimate connection between the repair material and the Emiaufbelag is achieved.
- the damaged area is processed prior to method step a) such that a repair site with a defined shape and size is produced.
- a repair site with a defined shape and size is produced.
- the diffusion donor layer applied to the repair site or the material filled in the repair site is usually film-like or lacquer-like or in the form of a slip or paste.
- the diffusion donor layer has as a donor metallic powder, in particular Al and / or Cr-containing powder. Other metallic powder compositions are conceivable. Usually, the metallic powder has a particle size distribution of 1 to 120 microns.
- the diffusion donor layer also contains at least one activator selected from the group: NH 4 F, NH 4 CL, AlF 3 , MgF 2 , CrCl 2 , CrCl 3 , LiF, phosphoric and chromic acid salts.
- the diffusion donor layer has at least one binder selected from the group consisting of polyvinyl alcohol, polyvinyl acetate, cellulose esters and acrylic dispersions.
- the diffusion donor layer usually contains water, alcohol and / or ether.
- a second hardening of the temperature material takes place by the heat treatment carried out in process step d). The heat treatment is carried out at temperatures between 500 ° C and 1250 ° C. If the diffusion donor layer comprises Al-containing powder, advantageously alitation of the repair material with the known advantages with respect to hardness, temperature, corrosion and oxidation resistance takes place.
- a post-processing and compensation of the repaired place of the inlet lining takes place after the process step d) a post-processing and compensation of the repaired place of the inlet lining.
- the figure shows schematically the procedure, which leads to a repair of a damaged area 10 of an inlet lining 12.
- the initial situation is shown under (I).
- the inlet lining 12 is applied to a base material 14, wherein the base material 14 is a compressor or turbine housing.
- the irregular damage of the inlet lining 12 resulting in (I) is processed such that a repair site 16 with a defined shape and size is formed (see (H)).
- the damaged area 10 or the defined repair point 16 of the inlet lining 12 is filled with a material 18.
- the material composition of the material 18 corresponds to that of the inlet lining 12 or is at least comparable with this.
- a slurry consisting of a binder and a metallic powder, by means of a brush or a spray gun applied.
- a corresponding drying of the filled material 18 a green body is formed, wherein the drying temperatures and drying times depend on the particular material composition.
- a diffusion donor layer 20 is applied over the area of the damaged site 10 or the defined repair site 16 and onto the filled-in material 18.
- the applied diffusion donor layer 20 is suitable for local diffusion coating of the material 18 as well as the non-damaged areas of the inlet pad 12 surrounding the repair site 10, 16.
- the donor-containing diffusion donor layer 20 contains Al-containing powder.
- the heat treatment carried out under (V) causes a local diffusion of at least one metallic element from the diffusion donor layer 20 into the material 18 and the areas of the inlet lining 12 which are covered by the diffusion donor layer 20 and adjoin the repair site 10, 16.
- the green body is cemented or Alitierung the material 18 and the adjacent areas of the inlet lining 12 by the use of said Al-containing powder. Due to the diffusion of the metallic elements is achieved that on the one hand an intimate connection between the material 18 and the inlet coating 12 is formed. On the other hand, in the material 18, the necessary hardness properties or the necessary temperature, oxidation and corrosion resistance are achieved.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006028297A DE102006028297A1 (en) | 2006-06-20 | 2006-06-20 | Method of repairing inlet coverings |
PCT/DE2007/001052 WO2007147387A2 (en) | 2006-06-20 | 2007-06-14 | Method of repairing intake coatings |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2035595A2 true EP2035595A2 (en) | 2009-03-18 |
Family
ID=38721011
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07764369A Withdrawn EP2035595A2 (en) | 2006-06-20 | 2007-06-14 | Method of repairing intake coatings |
Country Status (4)
Country | Link |
---|---|
US (1) | US9303522B2 (en) |
EP (1) | EP2035595A2 (en) |
DE (1) | DE102006028297A1 (en) |
WO (1) | WO2007147387A2 (en) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005058324A1 (en) * | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for producing an inlet lining |
GB0816255D0 (en) * | 2008-09-08 | 2008-10-15 | Rolls Royce Plc | A method of repairing an aluminide coating on an article |
GB0816257D0 (en) | 2008-09-08 | 2008-10-15 | Rolls Royce Plc | A method of repairing a coating on an article |
DE102009008510A1 (en) * | 2009-02-11 | 2010-08-12 | Mtu Aero Engines Gmbh | Coating and method for coating a workpiece |
US10006298B2 (en) * | 2009-09-08 | 2018-06-26 | Mtu Aero Engines Gmbh | Turbine blade of a gas turbine and method for coating a turbine blade of a gas turbine |
SG173932A1 (en) | 2010-02-25 | 2011-09-29 | United Technologies Corp | Repair of a coating on a turbine component |
ES2838026T3 (en) * | 2013-08-21 | 2021-07-01 | MTU Aero Engines AG | Procedure for coating a turbine component with a protective layer against wear |
US20150321297A1 (en) * | 2014-05-09 | 2015-11-12 | United Technologies Corporation | Systems and methods for repairing a surface of damaged metal components |
US10717166B2 (en) | 2016-12-02 | 2020-07-21 | General Electric Company | Motorized apparatus for use with rotary machines |
US10494926B2 (en) | 2017-08-28 | 2019-12-03 | General Electric Company | System and method for maintaining machines |
CN109604927B (en) * | 2018-12-19 | 2020-07-24 | 安徽泰尔表面工程技术有限公司 | Surfacing repair method for short-edge copper plate side surface of continuous casting crystallizer |
DE102019201658A1 (en) * | 2019-02-08 | 2020-08-13 | MTU Aero Engines AG | PROCEDURE FOR RENEWING AN INTAKE LAYERING OF A CASE-ELECTRIC POWER PLANT |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3053694A (en) * | 1961-02-20 | 1962-09-11 | Gen Electric | Abradable material |
US3817719A (en) * | 1971-07-09 | 1974-06-18 | United Aircraft Corp | High temperature abradable material and method of preparing the same |
US4409054A (en) * | 1981-01-14 | 1983-10-11 | United Technologies Corporation | Method for applying abradable material to a honeycomb structure and the product thereof |
DE4130946C1 (en) * | 1991-09-18 | 1992-09-03 | Mtu Muenchen Gmbh | |
US6022632A (en) | 1996-10-18 | 2000-02-08 | United Technologies | Low activity localized aluminide coating |
DE19827620C2 (en) * | 1998-06-20 | 2003-12-18 | Mtu Aero Engines Gmbh | Process for the production of armor for a metallic component and its use |
US6110262A (en) | 1998-08-31 | 2000-08-29 | Sermatech International, Inc. | Slurry compositions for diffusion coatings |
FR2830873B1 (en) * | 2001-10-16 | 2004-01-16 | Snecma Moteurs | PROTECTION PROCESS BY ALUMINIZATION OF METAL PARTS CONSTITUTED AT LEAST IN PART OF A HONEYCOMB STRUCTURE |
DE10259963B4 (en) | 2002-12-20 | 2010-04-01 | Mtu Aero Engines Gmbh | honeycomb seal |
GB2401117A (en) * | 2003-05-01 | 2004-11-03 | Rolls Royce Plc | A method of preventing aluminising and a mask to prevent aluminising |
DE10347363A1 (en) | 2003-10-11 | 2005-05-12 | Mtu Aero Engines Gmbh | Method for locally alitating, silicating or chromating metallic components |
US7390534B2 (en) * | 2003-10-31 | 2008-06-24 | General Electric Company | Diffusion coating process |
DE10356953B4 (en) | 2003-12-05 | 2016-01-21 | MTU Aero Engines AG | Inlet lining for gas turbines and method for producing the same |
-
2006
- 2006-06-20 DE DE102006028297A patent/DE102006028297A1/en not_active Ceased
-
2007
- 2007-06-14 WO PCT/DE2007/001052 patent/WO2007147387A2/en active Application Filing
- 2007-06-14 EP EP07764369A patent/EP2035595A2/en not_active Withdrawn
- 2007-06-14 US US12/308,523 patent/US9303522B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
US20100330271A1 (en) | 2010-12-30 |
WO2007147387A2 (en) | 2007-12-27 |
DE102006028297A1 (en) | 2007-12-27 |
US9303522B2 (en) | 2016-04-05 |
WO2007147387A3 (en) | 2008-04-10 |
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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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RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: WALTER, HEINRICH Inventor name: WERNER, ANDRE Inventor name: DAEUBLER, MANFRED, A. |
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17Q | First examination report despatched |
Effective date: 20090427 |
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RBV | Designated contracting states (corrected) |
Designated state(s): DE FR GB |
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Owner name: MTU AERO ENGINES AG |
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