US20090246011A1 - Film cooling of turbine components - Google Patents
Film cooling of turbine components Download PDFInfo
- Publication number
- US20090246011A1 US20090246011A1 US12/054,535 US5453508A US2009246011A1 US 20090246011 A1 US20090246011 A1 US 20090246011A1 US 5453508 A US5453508 A US 5453508A US 2009246011 A1 US2009246011 A1 US 2009246011A1
- Authority
- US
- United States
- Prior art keywords
- cooling
- flow
- turbine component
- hole
- diverter
- 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
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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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
Definitions
- the subject invention relates to turbines. More particularly, the subject invention relates to film cooling of turbine components.
- Components in the hot gas path of turbines are subjected to high temperatures which leads to low cycle fatigue cracking, creep rupture, and/or oxidation and the like which causes premature failure of the components.
- One or more methods are often employed to cool the hot gas path components to extend their useful lives.
- One such method is film cooling. Film cooling is accomplished by injecting air through holes in the surface of the component, from a source such as compressor bleed flow which bypasses a combustor. The relatively cooler air enters the hot gas path and forms an insulating layer between the hot gas and the component and reduces heat flux into the component.
- a turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface.
- a method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component.
- a cooling film is formed by the cooling flow between the flow path surface and a hot gas flow.
- FIG. 1 is a partial perspective view of an embodiment of a turbine component having flow diverters for film cooling
- FIG. 2 is a cross-sectional view of the turbine component of FIG. 1 ;
- FIG. 3 is an axial cross-sectional view of the turbine component of FIG. 1 ;
- FIG. 4 is a partial perspective view of another embodiment of a turbine component having flow diverters for film cooling
- FIG. 5 is a partial perspective view of an alternative embodiment of the turbine component of FIG. 4 ;
- FIG. 6 is a partial perspective view of yet another embodiment of a turbine component having flow diverters for film cooling.
- FIG. 1 A partial view of a turbine component, for example, a turbine airfoil 10 is shown in FIG. 1 .
- Hot gas flow 12 proceeds across an outer surface 14 of the turbine airfoil 10 in a flow direction 16 .
- At least one trench 18 is disposed in the turbine airfoil 10 and is defined by an upstream trench wall 20 which, in some embodiments extends substantially radially outward from the turbine airfoil 10 , and at least one downstream trench surface 22 .
- At least one cooling through hole 24 is disposed in the trench 18 .
- a plurality of cooling through holes 24 are arranged substantially in a line extending radially along the trench 18 , but other arrangements of cooling through holes 24 in the trench 18 are contemplated within the scope of the present disclosure.
- the cooling through holes 24 may have an elliptical opening as shown in FIG. 1 , or may have circular or other-shaped openings depending on desired flow from the cooling through holes 24 . Further, as shown in FIG. 2 , the cooling through holes 24 may have an axis 26 which is not perpendicular to the outer surface 14 , to facilitate smoother flow through the cooling through holes 24 .
- the downstream trench surface 22 slopes radially outwardly from a trench floor 28 . This prevents a cooling flow 30 exiting the cooling through holes 24 from blowing off of the outer surface 14 and into the hot gas flow 12 .
- At least one flow diverter 32 is disposed at the downstream trench surface 22 .
- Each flow diverter 32 includes a downstream wall 34 which, in the embodiment of FIG. 1 , is disposed axially downstream from and substantially perpendicular to the flow direction 16 such that cooling flow 30 exiting the cooling through hole 24 is diverted or split as shown in FIG. 1 .
- the downstream wall 34 is disposed at a substantially same lateral position as a corresponding cooling through hole 24 .
- the cooling flow 30 divides and flows laterally around the downstream wall 34 and along the downstream trench surface 22 . A portion of the cooling flow 30 may flow radially outboard of the downstream wall 34 and proceed along the outer surface 14 .
- Each flow diverter 32 includes two diverter sidewalls 36 . Each diverter sidewall 36 extends from the downstream wall 34 at a sidewall angle 38 which in some embodiments may be toward a diverter sidewall 36 of an adjacent flow diverter 32 . In the embodiment shown in FIG. 1 , the sidewall angles 38 are equal, but it is to be appreciated that embodiments where sidewall angles 38 differ for one or more sidewalls 36 are contemplated within the present scope.
- Utilizing flow diverters 32 causes the cooling flow 30 to spread over a greater portion of the turbine airfoil 10 thus providing more effective cooling of the turbine airfoil 10 .
- a width 40 of the downstream wall 32 and/or the sidewall angle 38 can be varied to provide a desired amount of spread of the cooling flow 28 .
- the diverter sidewalls 36 of adjacent flow diverters form a flow channel 42 preventing hot gas flow 12 from flowing between the cooling flow 30 and the downstream trench surface 22 thus preventing mixing of the hot gas flow 12 and the cooling flow 30 .
- each flow diverter 32 comprises two diverter sidewalls 36 converging at a vertex 44 located axially downstream from, and at a substantially same lateral position as a corresponding cooling through hole 24 such that cooling flow 30 exiting the cooling through hole 24 is split or diverted as shown in FIG. 4 .
- Each diverter sidewall 36 is disposed at a sidewall angle 38 and extends toward a diverter sidewall 36 of an adjacent flow diverter 32 .
- the flow diverter 32 including a vertex 44 prevents a vortex from forming in the cooling flow 30 at an exit of the cooling through hole 24 , as well as causes the cooling flow 30 to spread over a greater portion of the turbine airfoil 10 .
- each vertex 44 may be disposed at least partially within a corresponding cooling through hole 24 .
- a flow diverter 32 of this configuration is capable of splitting or diverting the cooling flow 30 as the cooling flow 30 exits the cooling through hole 24 .
- each flow diverter 32 is disposed laterally substantially between two cooling through holes 24 .
- each flow diverter 32 includes a downstream wall 34 and two diverter sidewalls 36 disposed at a sidewall angle 38 .
- the sidewall angles 38 are such that each diverter sidewall 36 extends toward convergence with the other diverter sidewall 36 of the same flow diverter 32 .
- the cooling flow 30 does not split upon exit from the cooling through hole 24 , but spreads across the flow channel 42 between adjacent flow diverters 32 .
- the cooling through holes 24 may have a number of shapes.
- the cooling through holes 24 shown in FIG. 6 include a diffusion surface 46 located at a downstream exit portion of the cooling through hole 24 and which slopes radially inward below the trench floor 28 .
- Cooling through holes 24 including the diffusion surface 46 provide additionally smooth transition of cooling flow 30 from the cooling through holes 24 to the outer surface 14 preventing blowing off of the cooling flow 30 into the hot gas flow 12 .
- an edge 48 of the diffusion surface is coplanar with the diverter sidewall 36 , but other configurations and alignments of the edge 48 relative to the diverter sidewall 36 are contemplated within the present scope.
- the turbine airfoil 10 comprises a substrate layer 50 and a coating layer 52 , which may include a thermal barrier coating (TBC) to provide additional thermal protection of the substrate layer 50 .
- TBC thermal barrier coating
- the cooling through holes 24 are disposed in the substrate layer 50 while the flow diverters 32 , upstream trench wall 20 and downstream trench surface 22 are disposed in the coating layer 52 and may be formed from TBC.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/054,535 US20090246011A1 (en) | 2008-03-25 | 2008-03-25 | Film cooling of turbine components |
JP2009057231A JP2009236112A (ja) | 2008-03-25 | 2009-03-11 | タービン部品のフィルム冷却 |
DE102009003634A DE102009003634A1 (de) | 2008-03-25 | 2009-03-17 | Filmkühlung von Turbinenkomponenten |
FR0951711A FR2929323A1 (fr) | 2008-03-25 | 2009-03-18 | Procede de refroidissement d'une piece de turbine et piece de turbine correspondante |
CN200910132498A CN101545381A (zh) | 2008-03-25 | 2009-03-25 | 涡轮机构件的薄膜冷却 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/054,535 US20090246011A1 (en) | 2008-03-25 | 2008-03-25 | Film cooling of turbine components |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090246011A1 true US20090246011A1 (en) | 2009-10-01 |
Family
ID=41011319
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/054,535 Abandoned US20090246011A1 (en) | 2008-03-25 | 2008-03-25 | Film cooling of turbine components |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090246011A1 (de) |
JP (1) | JP2009236112A (de) |
CN (1) | CN101545381A (de) |
DE (1) | DE102009003634A1 (de) |
FR (1) | FR2929323A1 (de) |
Cited By (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100329846A1 (en) * | 2009-06-24 | 2010-12-30 | Honeywell International Inc. | Turbine engine components |
US20110097188A1 (en) * | 2009-10-23 | 2011-04-28 | General Electric Company | Structure and method for improving film cooling using shallow trench with holes oriented along length of trench |
US20110123312A1 (en) * | 2009-11-25 | 2011-05-26 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
EP2557269A1 (de) * | 2011-08-08 | 2013-02-13 | Siemens Aktiengesellschaft | Filmkühlung von Turbinenbauteilen |
US20130045106A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Angled trench diffuser |
US8608443B2 (en) | 2010-06-11 | 2013-12-17 | Siemens Energy, Inc. | Film cooled component wall in a turbine engine |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
US8938879B2 (en) | 2011-02-14 | 2015-01-27 | General Electric Company | Components with cooling channels and methods of manufacture |
US9028207B2 (en) | 2010-09-23 | 2015-05-12 | Siemens Energy, Inc. | Cooled component wall in a turbine engine |
US9181819B2 (en) | 2010-06-11 | 2015-11-10 | Siemens Energy, Inc. | Component wall having diffusion sections for cooling in a turbine engine |
US9441488B1 (en) * | 2013-11-07 | 2016-09-13 | United States Of America As Represented By The Secretary Of The Air Force | Film cooling holes for gas turbine airfoils |
US20160281511A1 (en) * | 2012-11-16 | 2016-09-29 | Siemens Aktiengesellschaft | Modified surface around a hole |
US9631505B2 (en) | 2013-10-18 | 2017-04-25 | Rolls-Royce Deutschland Ltd & Co Kg | Device for cooling a wall of a component |
US9650900B2 (en) | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
US9957809B2 (en) | 2011-11-24 | 2018-05-01 | Siemens Aktiengesellschaft | Modified interface around a hole |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
CN108729953A (zh) * | 2018-04-24 | 2018-11-02 | 哈尔滨工程大学 | 一种在端壁气膜孔上游布置新月形沙丘凸台结构的涡轮 |
US10378444B2 (en) | 2015-08-19 | 2019-08-13 | General Electric Company | Engine component for a gas turbine engine |
US10570747B2 (en) * | 2017-10-02 | 2020-02-25 | DOOSAN Heavy Industries Construction Co., LTD | Enhanced film cooling system |
CN112443361A (zh) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | 一种用于涡轮叶片的凹坑逆向气膜孔结构 |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
US11118461B2 (en) * | 2018-03-29 | 2021-09-14 | Mitsubishi Power, Ltd. | Turbine rotor blade and gas turbine |
US11168570B1 (en) | 2020-08-27 | 2021-11-09 | Raytheon Technologies Corporation | Cooling arrangement for gas turbine engine components |
US11352902B2 (en) | 2020-08-27 | 2022-06-07 | Aytheon Technologies Corporation | Cooling arrangement including alternating pedestals for gas turbine engine components |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102140964B (zh) * | 2010-02-03 | 2013-07-03 | 中国科学院工程热物理研究所 | 一种提高离散孔气膜冷却效率的结构 |
US8727727B2 (en) * | 2010-12-10 | 2014-05-20 | General Electric Company | Components with cooling channels and methods of manufacture |
EP2489836A1 (de) | 2011-02-21 | 2012-08-22 | Karlsruher Institut für Technologie | Kühlbares Bauteil |
US8601691B2 (en) * | 2011-04-27 | 2013-12-10 | General Electric Company | Component and methods of fabricating a coated component using multiple types of fillers |
JP2013100771A (ja) * | 2011-11-08 | 2013-05-23 | Central Research Institute Of Electric Power Industry | 高温部品のフィルム冷却構造 |
US8858175B2 (en) * | 2011-11-09 | 2014-10-14 | General Electric Company | Film hole trench |
JP5696080B2 (ja) * | 2012-03-22 | 2015-04-08 | 三菱重工業株式会社 | 被冷却構造部材、タービン翼、及びタービン |
US9080451B2 (en) * | 2012-06-28 | 2015-07-14 | General Electric Company | Airfoil |
US20170089579A1 (en) * | 2015-09-30 | 2017-03-30 | General Electric Company | Cmc articles having small complex features for advanced film cooling |
US10830061B2 (en) * | 2016-03-31 | 2020-11-10 | Siemens Aktiengesellschaft | Turbine airfoil with internal cooling channels having flow splitter feature |
CN112145235B (zh) * | 2020-09-24 | 2021-08-20 | 大连理工大学 | 一种ω型回转腔层板冷却结构 |
CN112145234B (zh) * | 2020-09-24 | 2021-08-20 | 大连理工大学 | 一种ω型回转腔层板冷却结构 |
Citations (8)
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US5419681A (en) * | 1993-01-25 | 1995-05-30 | General Electric Company | Film cooled wall |
US5651662A (en) * | 1992-10-29 | 1997-07-29 | General Electric Company | Film cooled wall |
US5660525A (en) * | 1992-10-29 | 1997-08-26 | General Electric Company | Film cooled slotted wall |
US6234754B1 (en) * | 1999-08-09 | 2001-05-22 | United Technologies Corporation | Coolable airfoil structure |
US6234755B1 (en) * | 1999-10-04 | 2001-05-22 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture |
US6984100B2 (en) * | 2003-06-30 | 2006-01-10 | General Electric Company | Component and turbine assembly with film cooling |
US7553534B2 (en) * | 2006-08-29 | 2009-06-30 | General Electric Company | Film cooled slotted wall and method of making the same |
US20110097188A1 (en) * | 2009-10-23 | 2011-04-28 | General Electric Company | Structure and method for improving film cooling using shallow trench with holes oriented along length of trench |
-
2008
- 2008-03-25 US US12/054,535 patent/US20090246011A1/en not_active Abandoned
-
2009
- 2009-03-11 JP JP2009057231A patent/JP2009236112A/ja active Pending
- 2009-03-17 DE DE102009003634A patent/DE102009003634A1/de not_active Withdrawn
- 2009-03-18 FR FR0951711A patent/FR2929323A1/fr not_active Withdrawn
- 2009-03-25 CN CN200910132498A patent/CN101545381A/zh active Pending
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
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US5651662A (en) * | 1992-10-29 | 1997-07-29 | General Electric Company | Film cooled wall |
US5660525A (en) * | 1992-10-29 | 1997-08-26 | General Electric Company | Film cooled slotted wall |
US5419681A (en) * | 1993-01-25 | 1995-05-30 | General Electric Company | Film cooled wall |
US6234754B1 (en) * | 1999-08-09 | 2001-05-22 | United Technologies Corporation | Coolable airfoil structure |
US6234755B1 (en) * | 1999-10-04 | 2001-05-22 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture |
US6984100B2 (en) * | 2003-06-30 | 2006-01-10 | General Electric Company | Component and turbine assembly with film cooling |
US7553534B2 (en) * | 2006-08-29 | 2009-06-30 | General Electric Company | Film cooled slotted wall and method of making the same |
US20110097188A1 (en) * | 2009-10-23 | 2011-04-28 | General Electric Company | Structure and method for improving film cooling using shallow trench with holes oriented along length of trench |
Cited By (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8371814B2 (en) | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
US20100329846A1 (en) * | 2009-06-24 | 2010-12-30 | Honeywell International Inc. | Turbine engine components |
US20110097188A1 (en) * | 2009-10-23 | 2011-04-28 | General Electric Company | Structure and method for improving film cooling using shallow trench with holes oriented along length of trench |
US20110123312A1 (en) * | 2009-11-25 | 2011-05-26 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US8529193B2 (en) | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US8608443B2 (en) | 2010-06-11 | 2013-12-17 | Siemens Energy, Inc. | Film cooled component wall in a turbine engine |
US9181819B2 (en) | 2010-06-11 | 2015-11-10 | Siemens Energy, Inc. | Component wall having diffusion sections for cooling in a turbine engine |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
US9028207B2 (en) | 2010-09-23 | 2015-05-12 | Siemens Energy, Inc. | Cooled component wall in a turbine engine |
US8938879B2 (en) | 2011-02-14 | 2015-01-27 | General Electric Company | Components with cooling channels and methods of manufacture |
US9771804B2 (en) | 2011-08-08 | 2017-09-26 | Siemens Aktiengesellschaft | Film cooling of turbine blades or vanes |
EP2557269A1 (de) * | 2011-08-08 | 2013-02-13 | Siemens Aktiengesellschaft | Filmkühlung von Turbinenbauteilen |
EP2559855A3 (de) * | 2011-08-15 | 2014-08-27 | General Electric Company | Turbinenschaufel mit Filmkühllöcher sowie Verfahren zu deren Herstellung |
US20130045106A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Angled trench diffuser |
US9957809B2 (en) | 2011-11-24 | 2018-05-01 | Siemens Aktiengesellschaft | Modified interface around a hole |
US9650900B2 (en) | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
US20160281511A1 (en) * | 2012-11-16 | 2016-09-29 | Siemens Aktiengesellschaft | Modified surface around a hole |
US9631505B2 (en) | 2013-10-18 | 2017-04-25 | Rolls-Royce Deutschland Ltd & Co Kg | Device for cooling a wall of a component |
US9441488B1 (en) * | 2013-11-07 | 2016-09-13 | United States Of America As Represented By The Secretary Of The Air Force | Film cooling holes for gas turbine airfoils |
US10378444B2 (en) | 2015-08-19 | 2019-08-13 | General Electric Company | Engine component for a gas turbine engine |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
US11286791B2 (en) | 2016-05-19 | 2022-03-29 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
US10570747B2 (en) * | 2017-10-02 | 2020-02-25 | DOOSAN Heavy Industries Construction Co., LTD | Enhanced film cooling system |
US11002137B2 (en) * | 2017-10-02 | 2021-05-11 | DOOSAN Heavy Industries Construction Co., LTD | Enhanced film cooling system |
US11118461B2 (en) * | 2018-03-29 | 2021-09-14 | Mitsubishi Power, Ltd. | Turbine rotor blade and gas turbine |
CN108729953A (zh) * | 2018-04-24 | 2018-11-02 | 哈尔滨工程大学 | 一种在端壁气膜孔上游布置新月形沙丘凸台结构的涡轮 |
US11168570B1 (en) | 2020-08-27 | 2021-11-09 | Raytheon Technologies Corporation | Cooling arrangement for gas turbine engine components |
US11352902B2 (en) | 2020-08-27 | 2022-06-07 | Aytheon Technologies Corporation | Cooling arrangement including alternating pedestals for gas turbine engine components |
CN112443361A (zh) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | 一种用于涡轮叶片的凹坑逆向气膜孔结构 |
Also Published As
Publication number | Publication date |
---|---|
FR2929323A1 (fr) | 2009-10-02 |
JP2009236112A (ja) | 2009-10-15 |
DE102009003634A1 (de) | 2009-10-01 |
CN101545381A (zh) | 2009-09-30 |
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Legal Events
Date | Code | Title | Description |
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AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ITZEL, GARY MICHAEL;REEL/FRAME:020695/0195 Effective date: 20080317 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |