US20060110254A1 - Thermal barrier coating for turbine bucket platform side faces and methods of application - Google Patents
Thermal barrier coating for turbine bucket platform side faces and methods of application Download PDFInfo
- Publication number
- US20060110254A1 US20060110254A1 US10/995,272 US99527204A US2006110254A1 US 20060110254 A1 US20060110254 A1 US 20060110254A1 US 99527204 A US99527204 A US 99527204A US 2006110254 A1 US2006110254 A1 US 2006110254A1
- Authority
- US
- United States
- Prior art keywords
- platform
- thermal barrier
- barrier coating
- side faces
- 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
Links
Images
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
- F01D5/288—Protective coatings for blades
-
- 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX 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
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide 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
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
Definitions
- the present invention relates to a thermal barrier coating applied to side faces of the platform of a turbine bucket and methods of application.
- the bucket platforms did not require a coating to prevent oxidation distress due to firing temperatures.
- the firing temperatures were not sufficiently high to cause substantial distress.
- film cooling carryover from upstream nozzle side walls tended to lower the temperatures near the platforms from the resulting pitch line bias of the inlet temperature profile.
- platform surfaces exposed to the hot gas path have been provided with a thermal barrier coating.
- a need for minimizing the distress of the side faces of the platform which lie in generally circumferential registration with side faces of adjoining bucket platforms.
- a bucket for a turbine comprising: an airfoil, a root and a platform intermediate the airfoil and the root, the platform having generally circumferentially facing side faces for registration with generally corresponding side faces of adjacent buckets; each of the platform side faces having a groove therein opening circumferentially outwardly through the side faces; and a thermal barrier coating in the grooves and exposed along the side faces of the platform.
- a method of protecting side faces of a platform of a turbine bucket comprising the steps of: forming a groove along a side face of the platform opening circumferentially outwardly through the side faces; applying a bond coat to the groove; applying a thermal barrier coating to the bond coating; and removing a portion of the thermal bond coating along the side face to render side face portions having the applied thermal barrier coating thereon and bare metal to lie flush with one another.
- FIG. 1 is a perspective view of a turbine bucket illustrating a thermal barrier coating applied to the bucket platform surface and side faces of the bucket platform;
- FIG. 2 is a fragmentary cross-sectional view thereof, taken generally about on line 2 - 2 in FIG. 1 illustrating the application of a bond coat and thermal barrier coating to the bucket;
- FIG. 3 is a view similar to FIG. 2 illustrating the finished bucket with applied thermal barrier coating.
- FIG. 1 there is illustrated a turbine bucket generally designated 10 having an airfoil 12 , a platform 14 and a root portion 16 including a shank 18 and dovetail 20 .
- the turbine bucket 10 is typically arranged in an annular array of like turbine buckets on the rotor wheel of a turbine with the side faces 22 of the platform 14 generally circumferentially registering with corresponding side faces of circumferentially adjacent bucket platforms.
- the bucket surfaces are formed of bare metal.
- thermal barrier coatings per se have been used in the past. See, for example, U.S. Pat. Nos. 6,432,487; 6,047,539; and 5,830,586. As explained in detail below, any number of different types of thermal barrier coatings may be utilized in the present invention. For example, the yttria stabilized zirconia disclosed in U.S. Pat. No. 6,432,487 may be used.
- thermal barrier coatings are applied by a plasma spraying process usually in a number of layers and to a required thickness.
- interbucket or interplatform face gap which is necessary to be maintained to preclude arch binding of the buckets. That is, the buckets will tend to bind and distort when the buckets are subjected to high operating temperatures absent a gap between buckets in their cold condition.
- the side faces are provided with a thermal barrier coating.
- a groove 26 is formed along each of the opposite side edges of the platform. As illustrated in FIG. 2 , the groove 26 opens through the upper surface of the platform.
- a bond coat 28 is first applied to the bare metal to enhance the adhesion between the metal surface of the bucket platform and the thermal barrier coating.
- the bond coat 28 may comprise any available coating such as an oxidation resistancy alloy such as MCrALY where M is iron, cobalt and/or nickel or from a diffusion aluminide or platinum aluminide.
- the thermal barrier coating 30 is applied, preferably by plasma spraying the thermal barrier casting onto the bond coating, and preferably to a thickness which extends an outer portion of the thermal barrier coating beyond the side faces of the non-coated metal portions of the platform.
- the outer portion of the thermal barrier coating is then abraded or ground to remove a portion of the outer surface of the coating such that the thermal barrier coating lies flush with the remaining metal portions of the platform side faces.
- the grinding or abrading of the thermal barrier coating enables the designed interbucket side face gap to be maintained while simultaneously enabling the remaining thermal barrier coating to afford substantial resistance to distress as a result of the high temperatures to which the bucket is exposed during operation.
- the thermal barrier coating effectively reduces the heat flux from the hot gas path air which is ingested between bucket platforms.
- the present invention is applicable to turbine buckets in general, it is particularly applicable to steam cooled buckets where there is a lack of film cooling on upstream airfoils.
- the present invention is particularly applicable to closed loop steam cooled buckets but is also applicable to air-cooled buckets.
- the bond coat interface temperature has the potential for being lowered to levels which would preclude oxidation and enhance long term adhesion of the ceramic thermal barrier coating is the metal.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
- The present invention relates to a thermal barrier coating applied to side faces of the platform of a turbine bucket and methods of application.
- Over the years, gas turbines have trended towards increased inlet firing temperatures to improve output and engine efficiencies. As gas path temperatures have increased, bucket platforms have increasingly exhibited stress including oxidation, creep and low cycle fatigue cracking. In certain turbines using closed circuit steam cooling in the first two stages of buckets and nozzles, inlet profiles have become such that the platforms are staying close to peak inlet temperatures for the blade row. This exacerbates the potential distress on bucket platforms as the platforms run even hotter.
- In many older turbine designs, the bucket platforms did not require a coating to prevent oxidation distress due to firing temperatures. The firing temperatures were not sufficiently high to cause substantial distress. Also, film cooling carryover from upstream nozzle side walls tended to lower the temperatures near the platforms from the resulting pitch line bias of the inlet temperature profile. With the trend toward increasing firing temperatures, however, platform surfaces exposed to the hot gas path have been provided with a thermal barrier coating. However, there has also been discovered a need for minimizing the distress of the side faces of the platform which lie in generally circumferential registration with side faces of adjoining bucket platforms.
- In a preferred embodiment of the present invention there is provided a bucket for a turbine comprising: an airfoil, a root and a platform intermediate the airfoil and the root, the platform having generally circumferentially facing side faces for registration with generally corresponding side faces of adjacent buckets; each of the platform side faces having a groove therein opening circumferentially outwardly through the side faces; and a thermal barrier coating in the grooves and exposed along the side faces of the platform.
- In a further preferred embodiment of the present invention, there is provided a method of protecting side faces of a platform of a turbine bucket comprising the steps of: forming a groove along a side face of the platform opening circumferentially outwardly through the side faces; applying a bond coat to the groove; applying a thermal barrier coating to the bond coating; and removing a portion of the thermal bond coating along the side face to render side face portions having the applied thermal barrier coating thereon and bare metal to lie flush with one another.
-
FIG. 1 is a perspective view of a turbine bucket illustrating a thermal barrier coating applied to the bucket platform surface and side faces of the bucket platform; -
FIG. 2 is a fragmentary cross-sectional view thereof, taken generally about on line 2-2 inFIG. 1 illustrating the application of a bond coat and thermal barrier coating to the bucket; and -
FIG. 3 is a view similar toFIG. 2 illustrating the finished bucket with applied thermal barrier coating. - Referring now to the drawing figures, particularly to
FIG. 1 , there is illustrated a turbine bucket generally designated 10 having anairfoil 12, aplatform 14 and aroot portion 16 including ashank 18 anddovetail 20. It will be appreciated that theturbine bucket 10 is typically arranged in an annular array of like turbine buckets on the rotor wheel of a turbine with theside faces 22 of theplatform 14 generally circumferentially registering with corresponding side faces of circumferentially adjacent bucket platforms. Typically, the bucket surfaces are formed of bare metal. - While platform surfaces such as the
platform surface 24 illustrated inFIG. 1 have previously received a thermal barrier coating, the side faces 22 of the platform which lie in circumferential registration with side faces of adjacent bucket platforms, according to applicant's knowledge, have not previously been provided with a thermal barrier coating. Thermal barrier coatings per se have been used in the past. See, for example, U.S. Pat. Nos. 6,432,487; 6,047,539; and 5,830,586. As explained in detail below, any number of different types of thermal barrier coatings may be utilized in the present invention. For example, the yttria stabilized zirconia disclosed in U.S. Pat. No. 6,432,487 may be used. Typically, thermal barrier coatings are applied by a plasma spraying process usually in a number of layers and to a required thickness. - It will be appreciated that there is a well defined interbucket or interplatform face gap which is necessary to be maintained to preclude arch binding of the buckets. That is, the buckets will tend to bind and distort when the buckets are subjected to high operating temperatures absent a gap between buckets in their cold condition. To meet that requirement as well as to reduce the distress of the metal forming the side edges, i.e., slash faces of the platforms, the side faces are provided with a thermal barrier coating. To accomplish this, a
groove 26 is formed along each of the opposite side edges of the platform. As illustrated inFIG. 2 , thegroove 26 opens through the upper surface of the platform. To apply the thermal barrier coating to the opposite side edges, i.e., slash faces of the bucket platforms, abond coat 28 is first applied to the bare metal to enhance the adhesion between the metal surface of the bucket platform and the thermal barrier coating. Thebond coat 28 may comprise any available coating such as an oxidation resistancy alloy such as MCrALY where M is iron, cobalt and/or nickel or from a diffusion aluminide or platinum aluminide. - Once the bond coating has been applied, the
thermal barrier coating 30 is applied, preferably by plasma spraying the thermal barrier casting onto the bond coating, and preferably to a thickness which extends an outer portion of the thermal barrier coating beyond the side faces of the non-coated metal portions of the platform. The outer portion of the thermal barrier coating is then abraded or ground to remove a portion of the outer surface of the coating such that the thermal barrier coating lies flush with the remaining metal portions of the platform side faces. The grinding or abrading of the thermal barrier coating enables the designed interbucket side face gap to be maintained while simultaneously enabling the remaining thermal barrier coating to afford substantial resistance to distress as a result of the high temperatures to which the bucket is exposed during operation. - Thus, the foregoing application of the thermal barrier coating to portions of the side faces of the otherwise bare metal platform protects against oxidation and also reduces the thermal gradient during transients for the slash faces relative to the thin platform. The thermal barrier coating effectively reduces the heat flux from the hot gas path air which is ingested between bucket platforms.
- While the present invention is applicable to turbine buckets in general, it is particularly applicable to steam cooled buckets where there is a lack of film cooling on upstream airfoils. Thus, the present invention is particularly applicable to closed loop steam cooled buckets but is also applicable to air-cooled buckets. Also, with backside cooling of the platform, the bond coat interface temperature has the potential for being lowered to levels which would preclude oxidation and enhance long term adhesion of the ceramic thermal barrier coating is the metal.
- While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (9)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/995,272 US20060110254A1 (en) | 2004-11-24 | 2004-11-24 | Thermal barrier coating for turbine bucket platform side faces and methods of application |
DE102005055391A DE102005055391A1 (en) | 2004-11-24 | 2005-11-17 | Thermal barrier coating for the side surfaces of turbine blade platforms and application methods |
JP2005334184A JP2006144795A (en) | 2004-11-24 | 2005-11-18 | Turbine moving blade and its protection method |
CN200510127242.8A CN1782331A (en) | 2004-11-24 | 2005-11-24 | Thermal barrier coating for turbine bucket platform side faces and methods of application |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/995,272 US20060110254A1 (en) | 2004-11-24 | 2004-11-24 | Thermal barrier coating for turbine bucket platform side faces and methods of application |
Publications (1)
Publication Number | Publication Date |
---|---|
US20060110254A1 true US20060110254A1 (en) | 2006-05-25 |
Family
ID=36441874
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/995,272 Abandoned US20060110254A1 (en) | 2004-11-24 | 2004-11-24 | Thermal barrier coating for turbine bucket platform side faces and methods of application |
Country Status (4)
Country | Link |
---|---|
US (1) | US20060110254A1 (en) |
JP (1) | JP2006144795A (en) |
CN (1) | CN1782331A (en) |
DE (1) | DE102005055391A1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120195758A1 (en) * | 2011-01-31 | 2012-08-02 | Narendra Are | Methods and Systems For Controlling Thermal Differential In Turbine Systems |
US20120207613A1 (en) * | 2011-02-14 | 2012-08-16 | General Electric Company | Component of a turbine bucket platform |
US20130115096A1 (en) * | 2011-11-03 | 2013-05-09 | General Electric Company | Rotating airfoil component of a turbomachine |
US20150056061A1 (en) * | 2013-08-20 | 2015-02-26 | Kabushiki Kaisha Toshiba | Hydraulic turbine and pipe |
WO2015047485A3 (en) * | 2013-07-29 | 2015-06-18 | United Technologies Corporation | Gas turbine engine cmc airfoil assembly |
EP2918783A1 (en) * | 2014-03-12 | 2015-09-16 | Siemens Aktiengesellschaft | Turbine blade with a coated platform |
WO2016087215A1 (en) * | 2014-12-04 | 2016-06-09 | Siemens Aktiengesellschaft | Method for coating a turbine blade |
EP2881489B1 (en) | 2013-12-05 | 2016-07-27 | General Electric Company | Coating method |
US9869183B2 (en) | 2014-08-01 | 2018-01-16 | United Technologies Corporation | Thermal barrier coating inside cooling channels |
US20220349314A1 (en) * | 2021-05-03 | 2022-11-03 | Raytheon Technologies Corporation | Variable thickness machinable coating for platform seals |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2096263A1 (en) * | 2008-02-29 | 2009-09-02 | Siemens Aktiengesellschaft | Droplet impact protection layer for a blade |
FR2985759B1 (en) * | 2012-01-17 | 2014-03-07 | Snecma | MOBILE AUB OF TURBOMACHINE |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6432487B1 (en) * | 2000-12-28 | 2002-08-13 | General Electric Company | Dense vertically cracked thermal barrier coating process to facilitate post-coat surface finishing |
US20020127111A1 (en) * | 2001-03-06 | 2002-09-12 | Mitsubishi Heavy Industries Ltd. | Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine |
-
2004
- 2004-11-24 US US10/995,272 patent/US20060110254A1/en not_active Abandoned
-
2005
- 2005-11-17 DE DE102005055391A patent/DE102005055391A1/en not_active Withdrawn
- 2005-11-18 JP JP2005334184A patent/JP2006144795A/en not_active Withdrawn
- 2005-11-24 CN CN200510127242.8A patent/CN1782331A/en active Pending
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6432487B1 (en) * | 2000-12-28 | 2002-08-13 | General Electric Company | Dense vertically cracked thermal barrier coating process to facilitate post-coat surface finishing |
US20020127111A1 (en) * | 2001-03-06 | 2002-09-12 | Mitsubishi Heavy Industries Ltd. | Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8784061B2 (en) * | 2011-01-31 | 2014-07-22 | General Electric Company | Methods and systems for controlling thermal differential in turbine systems |
US20120195758A1 (en) * | 2011-01-31 | 2012-08-02 | Narendra Are | Methods and Systems For Controlling Thermal Differential In Turbine Systems |
US20120207613A1 (en) * | 2011-02-14 | 2012-08-16 | General Electric Company | Component of a turbine bucket platform |
US8662849B2 (en) * | 2011-02-14 | 2014-03-04 | General Electric Company | Component of a turbine bucket platform |
EP2487331A3 (en) * | 2011-02-14 | 2017-03-22 | General Electric Company | Component of a turbine bucket platform |
US20130115096A1 (en) * | 2011-11-03 | 2013-05-09 | General Electric Company | Rotating airfoil component of a turbomachine |
US8967957B2 (en) * | 2011-11-03 | 2015-03-03 | General Electric Company | Rotating airfoil component of a turbomachine |
WO2015047485A3 (en) * | 2013-07-29 | 2015-06-18 | United Technologies Corporation | Gas turbine engine cmc airfoil assembly |
US10125620B2 (en) | 2013-07-29 | 2018-11-13 | United Technologies Corporation | Gas turbine engine CMC airfoil assembly |
US10087906B2 (en) * | 2013-08-20 | 2018-10-02 | Kabushiki Kaisha Toshiba | Hydraulic turbine and pipe |
US20150056061A1 (en) * | 2013-08-20 | 2015-02-26 | Kabushiki Kaisha Toshiba | Hydraulic turbine and pipe |
EP2881489B1 (en) | 2013-12-05 | 2016-07-27 | General Electric Company | Coating method |
EP2918783A1 (en) * | 2014-03-12 | 2015-09-16 | Siemens Aktiengesellschaft | Turbine blade with a coated platform |
US9869183B2 (en) | 2014-08-01 | 2018-01-16 | United Technologies Corporation | Thermal barrier coating inside cooling channels |
WO2016087215A1 (en) * | 2014-12-04 | 2016-06-09 | Siemens Aktiengesellschaft | Method for coating a turbine blade |
US20220349314A1 (en) * | 2021-05-03 | 2022-11-03 | Raytheon Technologies Corporation | Variable thickness machinable coating for platform seals |
US12000288B2 (en) * | 2021-05-03 | 2024-06-04 | Rtx Corporation | Variable thickness machinable coating for platform seals |
Also Published As
Publication number | Publication date |
---|---|
CN1782331A (en) | 2006-06-07 |
DE102005055391A1 (en) | 2006-06-08 |
JP2006144795A (en) | 2006-06-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ITZEL, GARY MICHAEL;JACALA, ARIEL CAESAR-PREPENA;REEL/FRAME:016025/0959 Effective date: 20041119 |
|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ITZEL, GARY MICHAEL;JACALA, ARIEL CAESAR-PREPENA;REEL/FRAME:017494/0422 Effective date: 20041119 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |