US20090269207A1 - Component, in particular, a gas turbine component - Google Patents

Component, in particular, a gas turbine component Download PDF

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Publication number
US20090269207A1
US20090269207A1 US11/908,092 US90809206A US2009269207A1 US 20090269207 A1 US20090269207 A1 US 20090269207A1 US 90809206 A US90809206 A US 90809206A US 2009269207 A1 US2009269207 A1 US 2009269207A1
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US
United States
Prior art keywords
main body
gas turbine
barrier coat
turbine component
protection coating
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
US11/908,092
Inventor
Wolfgang Eichmann
Falko Heutling
Karl-Heinz Manier
Markus Uecker
Thomas Uihlein
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: UECKER, MARKUS, EICHMANN, WOLFGANG, UIHLEIN, THOMAS
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH CORRECTIVE ASSIGNMENT TO CORRECT THE CONVEYING PARTY DATA PREVIOUSLY RECORDED ON REEL 019856 FRAME 0038. ASSIGNOR(S) HEREBY CONFIRMS THE CONVEYANCE TEXT. Assignors: MANIER, KARL-HEINZ, UECKER, MARKUS, EICHMANN, WOLFGANG, HEUTLING, FALKO, UIHLEIN, THOMAS
Publication of US20090269207A1 publication Critical patent/US20090269207A1/en
Abandoned legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/023—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material only coatings of metal elements only
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/131—Molybdenum
    • 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
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a component, specifically a component for a gas turbine.
  • Components for a gas turbine such as the rotor blades, are given special wear protection coatings to provide oxidation resistance, corrosion resistance or erosion resistance.
  • the components of gas turbines are subject to wear during operation or can be damaged in other ways.
  • To repair damage it is usually necessary to remove or strip the wear protection coating from the component to be repaired in specific areas, partially or even completely.
  • the removal or stripping of coatings is also called decoating.
  • decoating processes a distinction is made between those in which the decoating is carried out by mechanical means, chemical means or electrochemical means.
  • the problem underlying the present invention is to create a novel component, specifically a novel component for a gas turbine.
  • a resistive layer is located between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
  • the protection coating protects the main body of the component from attack from the decoating during chemical or electrochemical decoating. To this extent, there is no further risk during chemical or electrochemical decoating of such a component that the material properties of the base material are negatively affected.
  • the protection coating is resistant to chemical and electrochemical decoating.
  • the barrier coating has a material composition matched to the material composition of the main body, where the material of the barrier coating is alloyed, or enriched with an element relative to the base material of the main body from the platinum group and/or with nickel and/or with molybdenum.
  • FIG. 1 shows a schematic cross-section through the component in accordance with the invention.
  • FIG. 1 the invention is described in greater detail with reference to FIG. 1 .
  • FIG. 1 shows a schematic cross-section through a component 10 in accordance with the invention, where the component 10 consists of a main body 11 and a wear protection coating 12 applied to a surface of the main body 11 .
  • the wear protection coating 12 is a multi-layer, or multi-coat, wear protection coating 12 consisting of layers 13 , 14 , and 15 .
  • the layers 13 , 14 , and 15 of the wear protection coating may be alternately relatively hard or relatively soft layers, or coats. There can be any number of layers in the wear protection coating 12 and this is of subordinate importance for the present invention.
  • a barrier coat 16 is positioned between the wear protection coating 12 and the main body 11 of the component 10 in accordance with the invention.
  • the barrier coat 16 is located between the main body 11 and the lowest, or innermost, layer 13 of the wear protection coating 12 .
  • the barrier coat 16 assumes the function of protecting the main body 11 during chemical or electrochemical decoating.
  • the barrier coat 16 is therefore resistant to chemical or electrochemical decoating and is not attacked, or removed, during such a decoating so that the base material of the main body 11 is not attacked or removed.
  • the barrier coat 16 has a material composition which is matched to the material composition of the main body 11 .
  • both the main body 11 as well as the barrier coat 16 are made from a titanium-based alloy.
  • the material of the barrier coat 16 is enriched or alloyed with at least one element from the platinum group and/or with nickel and/or molybdenum relative to the base material of the main body 11 .
  • the material of the barrier coat 16 may have platinum in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have palladium in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have nickel in a percentage of at least 0.50% by weight and/or molybdenum in a percentage of at least 4.00% by weight. One or even more of these elements may be present in the above specified proportions in the barrier coat 16 .
  • the barrier coat protects the base material of the main body against attack during chemical or electrochemical decoating of the component. This ensures that during decoating the material properties of the base material of the main body are not negatively affected.
  • An additional advantage of the barrier coat is that it is relatively smooth. Thus, following decoating a newly applied wear protection coating is able to adhere better to the base body than would have been possible with decoating in the case of a main body attacked or etched during decoating from the state of the art. Since the barrier coat has a material composition matched to the material composition of the main body there are no matching problems for the wear protection coating.

Abstract

A component, specifically a component for a gas turbine, having a main body of a base material and a wear protection coating applied to a surface of the main body, specifically a protective coating against corrosion and/or oxidation and/or erosion, is disclosed. A barrier coat is applied between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.

Description

    BACKGROUND AND SUMMARY OF THE INVENTION
  • This application claims the priority of International Application No. PCT/DE2006/000379, filed Mar. 3, 2006, and German Patent Document No. 10 2005 011 011.8, filed Mar. 10, 2005, the disclosures of which are expressly incorporated by reference herein.
  • The invention relates to a component, specifically a component for a gas turbine.
  • Components for a gas turbine, such as the rotor blades, are given special wear protection coatings to provide oxidation resistance, corrosion resistance or erosion resistance. The components of gas turbines are subject to wear during operation or can be damaged in other ways. To repair damage it is usually necessary to remove or strip the wear protection coating from the component to be repaired in specific areas, partially or even completely. The removal or stripping of coatings is also called decoating. In the decoating processes a distinction is made between those in which the decoating is carried out by mechanical means, chemical means or electrochemical means.
  • With chemical or even electrochemical decoating of a component the risk exists that the basic material of the main body coated with the wear-protection coating will be attacked or removed. With some base materials, such as titanium alloys, this can result in a deterioration of the material properties. In the case of titanium alloys the HCF strength may be reduced. Consequently, in accordance with the prior art, expensive steps must be taken in the decoating of components to prevent the basic material of the main body from being attacked.
  • With this as the starting point, the problem underlying the present invention is to create a novel component, specifically a novel component for a gas turbine.
  • In accordance with the invention, a resistive layer is located between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
  • Within the meaning of the present invention it is provided to locate a resistive layer between the main body and the wear protection coating for a coated component. The protection coating protects the main body of the component from attack from the decoating during chemical or electrochemical decoating. To this extent, there is no further risk during chemical or electrochemical decoating of such a component that the material properties of the base material are negatively affected. The protection coating is resistant to chemical and electrochemical decoating.
  • Preferably the barrier coating has a material composition matched to the material composition of the main body, where the material of the barrier coating is alloyed, or enriched with an element relative to the base material of the main body from the platinum group and/or with nickel and/or with molybdenum.
  • Preferred further developments of the invention emerge from the subsequent description. An embodiment of the invention, without being limited thereto, is described in more detail using the drawing.
    • BRIEF DESCRIPTION OF THE DRAWING
  • FIG. 1 shows a schematic cross-section through the component in accordance with the invention.
    •  DETAILED DESCRIPTION OF THE DRAWING
  • Hereinafter the invention is described in greater detail with reference to FIG. 1.
  • FIG. 1 shows a schematic cross-section through a component 10 in accordance with the invention, where the component 10 consists of a main body 11 and a wear protection coating 12 applied to a surface of the main body 11. In the embodiment shown the wear protection coating 12 is a multi-layer, or multi-coat, wear protection coating 12 consisting of layers 13, 14, and 15. The layers 13, 14, and 15 of the wear protection coating may be alternately relatively hard or relatively soft layers, or coats. There can be any number of layers in the wear protection coating 12 and this is of subordinate importance for the present invention.
  • Within the meaning of the present invention, a barrier coat 16 is positioned between the wear protection coating 12 and the main body 11 of the component 10 in accordance with the invention. The barrier coat 16 is located between the main body 11 and the lowest, or innermost, layer 13 of the wear protection coating 12. The barrier coat 16 assumes the function of protecting the main body 11 during chemical or electrochemical decoating. The barrier coat 16 is therefore resistant to chemical or electrochemical decoating and is not attacked, or removed, during such a decoating so that the base material of the main body 11 is not attacked or removed.
  • The barrier coat 16 has a material composition which is matched to the material composition of the main body 11. Preferably both the main body 11 as well as the barrier coat 16 are made from a titanium-based alloy. The material of the barrier coat 16 is enriched or alloyed with at least one element from the platinum group and/or with nickel and/or molybdenum relative to the base material of the main body 11.
  • Thus the material of the barrier coat 16 may have platinum in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have palladium in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have nickel in a percentage of at least 0.50% by weight and/or molybdenum in a percentage of at least 4.00% by weight. One or even more of these elements may be present in the above specified proportions in the barrier coat 16.
  • As already mentioned, the barrier coat protects the base material of the main body against attack during chemical or electrochemical decoating of the component. This ensures that during decoating the material properties of the base material of the main body are not negatively affected. An additional advantage of the barrier coat is that it is relatively smooth. Thus, following decoating a newly applied wear protection coating is able to adhere better to the base body than would have been possible with decoating in the case of a main body attacked or etched during decoating from the state of the art. Since the barrier coat has a material composition matched to the material composition of the main body there are no matching problems for the wear protection coating.

Claims (12)

1-8. (canceled)
9. Gas turbine component, having a main body made of a base material and a wear protection coating against corrosion and/or oxidation and/or erosion applied to a surface of the main body and a barrier coat applied between the main body and the wear protection coating, wherein the barrier coat is configured with a relatively smooth surface and is resistant to chemical or electrochemical decoating and wherein the wear protection coating is multi-layered.
10. The gas turbine component according to claim 9, wherein the barrier coat has a material composition matching a material composition of the main body.
11. The gas turbine component according to claim 9, wherein a material of the barrier coat, compared with the base material of the main body is enriched or alloyed with at least one element from a platinum group and/or with nickel and/or with molybdenum.
12. The gas turbine component according to claim 11, wherein the material of the barrier coat contains platinum in an amount of at least 0.05% by weight.
13. The gas turbine component according to claim 11, wherein the material of the barrier coat contains palladium in an amount of at least 0.05% by weight.
14. The gas turbine component according to claim 11, wherein the material of the barrier coat contains nickel in an amount of at least 0.50% by weight.
15. The gas turbine component according to claim 11, wherein the material of the barrier coat contains molybdenum in an amount of at least 4.00% by weight.
16. The gas turbine component according to claim 9, wherein the base material of the main body and a material of the barrier coat are titanium alloys.
17. A gas turbine component, comprising:
a main body;
a wear protection coating, wherein the wear protection coating includes a plurality of layers; and
a barrier coat disposed between the main body and the wear protection coating, wherein the barrier coat includes a smooth surface and is resistant to chemical or electrochemical decoating.
18. The gas turbine component according to claim 17, wherein the wear protection coating provides a protection of the main body against corrosion and/or oxidation and/or erosion.
19. The gas turbine component according to claim 17, wherein the barrier coat has a material composition matched to a material composition of the main body.
US11/908,092 2005-03-10 2006-03-03 Component, in particular, a gas turbine component Abandoned US20090269207A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102005011011.8 2005-03-10
DE102005011011A DE102005011011A1 (en) 2005-03-10 2005-03-10 Component, in particular gas turbine component
PCT/DE2006/000379 WO2006094481A1 (en) 2005-03-10 2006-03-03 Component, in particular, a gas turbine component

Publications (1)

Publication Number Publication Date
US20090269207A1 true US20090269207A1 (en) 2009-10-29

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US11/908,092 Abandoned US20090269207A1 (en) 2005-03-10 2006-03-03 Component, in particular, a gas turbine component

Country Status (5)

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US (1) US20090269207A1 (en)
EP (1) EP1856306A1 (en)
CA (1) CA2600198A1 (en)
DE (1) DE102005011011A1 (en)
WO (1) WO2006094481A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9689069B2 (en) 2014-03-12 2017-06-27 Rolls-Royce Corporation Coating system including diffusion barrier layer including iridium and oxide layer
US9719353B2 (en) 2011-04-13 2017-08-01 Rolls-Royce Corporation Interfacial diffusion barrier layer including iridium on a metallic substrate

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015208781A1 (en) * 2015-05-12 2016-11-17 MTU Aero Engines AG Combination of blade tip armor and erosion control layer and method of making the same

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US6071627A (en) * 1996-03-29 2000-06-06 Kabushiki Kaisha Toshiba Heat-resistant member and a method for evaluating quality of a heat-resistant member
US6475642B1 (en) * 2000-08-31 2002-11-05 General Electric Company Oxidation-resistant coatings, and related articles and processes
US6620525B1 (en) * 2000-11-09 2003-09-16 General Electric Company Thermal barrier coating with improved erosion and impact resistance and process therefor
US20040033311A1 (en) * 2002-03-09 2004-02-19 Erwin Bayer Method for removing coating from power unit components and device for carrying out the method
US6830827B2 (en) * 2000-03-07 2004-12-14 Ebara Corporation Alloy coating, method for forming the same, and member for high temperature apparatuses
US20090176110A1 (en) * 2008-01-08 2009-07-09 General Electric Company Erosion and corrosion-resistant coating system and process therefor

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DE58908611D1 (en) * 1989-08-10 1994-12-08 Siemens Ag HIGH-TEMPERATURE-RESISTANT CORROSION PROTECTION COATING, IN PARTICULAR FOR GAS TURBINE COMPONENTS.
EP0872575A2 (en) * 1997-04-19 1998-10-21 Institut für Festkörper- und Werkstofforschung Dresden e.V. Protective surface coating for titanium alloys
US6969457B2 (en) * 2002-10-21 2005-11-29 General Electric Company Method for partially stripping a coating from the surface of a substrate, and related articles and compositions
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US6071627A (en) * 1996-03-29 2000-06-06 Kabushiki Kaisha Toshiba Heat-resistant member and a method for evaluating quality of a heat-resistant member
US6830827B2 (en) * 2000-03-07 2004-12-14 Ebara Corporation Alloy coating, method for forming the same, and member for high temperature apparatuses
US6475642B1 (en) * 2000-08-31 2002-11-05 General Electric Company Oxidation-resistant coatings, and related articles and processes
US6620525B1 (en) * 2000-11-09 2003-09-16 General Electric Company Thermal barrier coating with improved erosion and impact resistance and process therefor
US20040033311A1 (en) * 2002-03-09 2004-02-19 Erwin Bayer Method for removing coating from power unit components and device for carrying out the method
US20090176110A1 (en) * 2008-01-08 2009-07-09 General Electric Company Erosion and corrosion-resistant coating system and process therefor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9719353B2 (en) 2011-04-13 2017-08-01 Rolls-Royce Corporation Interfacial diffusion barrier layer including iridium on a metallic substrate
US9689069B2 (en) 2014-03-12 2017-06-27 Rolls-Royce Corporation Coating system including diffusion barrier layer including iridium and oxide layer

Also Published As

Publication number Publication date
WO2006094481A1 (en) 2006-09-14
DE102005011011A1 (en) 2006-09-14
EP1856306A1 (en) 2007-11-21
CA2600198A1 (en) 2006-09-14

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AS Assignment

Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:EICHMANN, WOLFGANG;UECKER, MARKUS;UIHLEIN, THOMAS;REEL/FRAME:019856/0038;SIGNING DATES FROM 20070827 TO 20070905

AS Assignment

Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE CONVEYING PARTY DATA PREVIOUSLY RECORDED ON REEL 019856 FRAME 0038;ASSIGNORS:EICHMANN, WOLFGANG;MANIER, KARL-HEINZ;UECKER, MARKUS;AND OTHERS;REEL/FRAME:020136/0046;SIGNING DATES FROM 20070827 TO 20070907

STCB Information on status: application discontinuation

Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION