US20120051924A1 - Turbine Blade Assembly - Google Patents
Turbine Blade Assembly Download PDFInfo
- Publication number
- US20120051924A1 US20120051924A1 US12/872,901 US87290110A US2012051924A1 US 20120051924 A1 US20120051924 A1 US 20120051924A1 US 87290110 A US87290110 A US 87290110A US 2012051924 A1 US2012051924 A1 US 2012051924A1
- Authority
- US
- United States
- Prior art keywords
- blade assembly
- section
- airfoil
- rotor
- attachment section
- 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
- 238000000034 method Methods 0.000 claims abstract description 11
- 230000000712 assembly Effects 0.000 claims description 6
- 238000000429 assembly Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 4
- 239000011153 ceramic matrix composite Substances 0.000 claims description 3
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 239000013078 crystal Substances 0.000 claims description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000007779 soft material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F05D2230/60—Assembly methods
- F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
-
- 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
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- the subject matter disclosed herein relates to turbomachines. More specifically, the subject disclosure relates to turbine blade assemblies for turbomachines.
- Turbine assemblies include a number of blades secured to a rotor.
- the combined airfoil/platform blade assembly is secured to the rotor via, for example, a conventional dovetail attachment.
- Blade assemblies where the airfoil portion and the platform portion are of differing materials having differing mechanical and thermal characteristics that introduce thermal matching problems as well as issues regarding the mechanical integrity of the assembly.
- the airfoil portions are typically secured to the platform portions also via dovetails, often in an axial direction. This introduces leakage paths through the turbomachine, for which additional sealing structures must be introduced to control the leakage. As such, the part count and therefore cost of the turbomachine increases.
- the art would well receive a turbine blade assembly that is cost effective and does not greatly negatively impact leakage through the turbomachine.
- a blade assembly for a rotor includes an attachment section operably connectable to a rotor, and an airfoil section. At least one retainer extends in a substantially tangential direction at least partially through the airfoil section and the attachment section to secure the airfoil section to the attachment section.
- a method of assembling a rotor assembly includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section of a blade assembly and an airfoil section of the blade assembly, thereby securing the airfoil section to the attachment section. The blade assembly is then secured to a rotor.
- FIG. 1 is a partial plan view of an embodiment of a rotor assembly
- FIG. 2 is an exploded view of an embodiment of a blade assembly for a rotor assembly
- FIG. 3 is a cross-sectional view of an embodiment of a blade assembly for a rotor assembly.
- FIG. 1 Shown in FIG. 1 is an embodiment of a rotor assembly 10 for, for example, a turbine of a turbomachine.
- the rotor assembly 10 includes a plurality of blade assemblies 12 secured to a rotor 14 at a periphery of the rotor 14 via, for example, a plurality of dovetail attachments 16 .
- a blade assembly 12 includes an airfoil section 18 and an attachment section 20 .
- the airfoil section 18 includes an airfoil 22 and, in some embodiments, a platform 24 which defines an annular flowpath of the rotor 14 .
- the airfoil section 18 may be formed from a variety of materials, which are well suited to the high temperature environment in which many rotors 14 operate.
- the airfoil section 18 may be formed from a ceramic matrix composite (CMC), or a single crystal alloy.
- the attachment section 20 is formed separately from the airfoil section 18 and may be formed from a material different than that utilized in the airfoil section 18 .
- the attachment section 20 includes an attachment feature to secure the blade assembly to the rotor 14 , which in some embodiments is the dovetail 16 .
- the attachment section 20 includes a web portion 26 , which in some embodiments, extends in a substantially axial direction along the attachment section 20 .
- the web portion 26 includes a pocket 28 into which a tab 30 of the airfoil section 18 is inserted.
- the pocket 28 includes one or more pocket holes 32 through at least one wall of the pocket 28 . As shown in FIG. 2 , in some embodiments the pocket hole 32 extends through an axially-extending sidewall 34 of the pocket 28 . Although the embodiment of FIG. 2 includes one pocket hole 32 , it is to be appreciated that two or more pocket holes 32 may be included.
- the tab 30 includes at least one tab hole 36 extending therethrough and substantially aligned with the one or more pocket holes 32 . While the tab hole 36 and the pocket hole 32 shown in FIG. 2 are round, it is to be appreciated that the tab hole 36 and/or the pocket hole 32 may be other shapes, for example oval or angular.
- One or more retainers for example, blade pins 38 are included to secure the airfoil section 18 to the attachment section 20 .
- Each blade pin 38 extends tangentially through the pocket hole 32 and at least partially through the tab hole 36 .
- the blade pin 38 extends through the pocket hole 32 at a first sidewall 34 of the pocket 28 and through the tab hole 36 .
- a second sidewall 34 of the pocket is without a pocket hole 32 so that a tip 40 of the blade pin 38 does not pass entirely through the pocket 28 .
- the sidewall 34 of the adjacent blade assembly 12 may substantially abut a head 42 of the blade pin 38 to retain the blade pin 38 in the blade assembly 12 .
- the blade pin may be retained in the blade assembly 12 via a process such as welding, or other retention means.
- the blade pin 38 may be assembled to the blade assembly 12 via a press fit. Even though a blade pin 38 is utilized in the illustrated embodiment of FIG. 3 , it is to be appreciated that other means for securing the airfoil section 18 to the attachment section 20 , including mechanical threaded fasteners, wedges, welding, and/or adhesives.
- the blade assembly 12 includes a bushing 44 installed into the pocket holes 32 and tab holes 36 prior to installing the blade pin 38 .
- Use of the bushing 44 reduces hertz stresses on the blade assembly 12 in the area of the blade pin 38 .
- a sleeve 46 comprising for example, a relatively soft material, is disposed between the tab 30 and the pocket 28 .
- the sleeve 46 is utilized to reduce stresses and wear on the tab 30 and the pocket 28 at the interfaces between the tab 30 and the pocket 28 .
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The subject invention was conceived under United States Government contract DE-FC26-05NT42643-DOE. The Federal Government may have certain rights to this invention.
- The subject matter disclosed herein relates to turbomachines. More specifically, the subject disclosure relates to turbine blade assemblies for turbomachines.
- Turbine assemblies include a number of blades secured to a rotor. In some turbines, it is desirable for the blade to include an airfoil portion and a platform portion into which the airfoil portion is inserted, often in order to allow the airfoil portion and the platform portion to be formed from different materials. The combined airfoil/platform blade assembly is secured to the rotor via, for example, a conventional dovetail attachment.
- Blade assemblies where the airfoil portion and the platform portion are of differing materials having differing mechanical and thermal characteristics that introduce thermal matching problems as well as issues regarding the mechanical integrity of the assembly. In such assemblies the airfoil portions are typically secured to the platform portions also via dovetails, often in an axial direction. This introduces leakage paths through the turbomachine, for which additional sealing structures must be introduced to control the leakage. As such, the part count and therefore cost of the turbomachine increases. The art would well receive a turbine blade assembly that is cost effective and does not greatly negatively impact leakage through the turbomachine.
- According to one aspect of the invention, a blade assembly for a rotor includes an attachment section operably connectable to a rotor, and an airfoil section. At least one retainer extends in a substantially tangential direction at least partially through the airfoil section and the attachment section to secure the airfoil section to the attachment section.
- According to another aspect of the invention, a method of assembling a rotor assembly includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section of a blade assembly and an airfoil section of the blade assembly, thereby securing the airfoil section to the attachment section. The blade assembly is then secured to a rotor.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
-
FIG. 1 is a partial plan view of an embodiment of a rotor assembly; -
FIG. 2 is an exploded view of an embodiment of a blade assembly for a rotor assembly; and -
FIG. 3 is a cross-sectional view of an embodiment of a blade assembly for a rotor assembly. - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
- Shown in
FIG. 1 is an embodiment of arotor assembly 10 for, for example, a turbine of a turbomachine. Therotor assembly 10 includes a plurality ofblade assemblies 12 secured to arotor 14 at a periphery of therotor 14 via, for example, a plurality ofdovetail attachments 16. - Referring to the exploded view of
FIG. 2 , ablade assembly 12 includes anairfoil section 18 and anattachment section 20. Theairfoil section 18 includes anairfoil 22 and, in some embodiments, aplatform 24 which defines an annular flowpath of therotor 14. Theairfoil section 18 may be formed from a variety of materials, which are well suited to the high temperature environment in whichmany rotors 14 operate. For example, theairfoil section 18 may be formed from a ceramic matrix composite (CMC), or a single crystal alloy. Theattachment section 20 is formed separately from theairfoil section 18 and may be formed from a material different than that utilized in theairfoil section 18. Since the environment of theattachment section 20 is not as high temperature as that of theairfoil section 18, lower cost metallic materials such as nickel alloys may be used. Theattachment section 20 includes an attachment feature to secure the blade assembly to therotor 14, which in some embodiments is thedovetail 16. - The
attachment section 20 includes aweb portion 26, which in some embodiments, extends in a substantially axial direction along theattachment section 20. Theweb portion 26 includes apocket 28 into which atab 30 of theairfoil section 18 is inserted. Thepocket 28 includes one or more pocket holes 32 through at least one wall of thepocket 28. As shown inFIG. 2 , in some embodiments thepocket hole 32 extends through an axially-extendingsidewall 34 of thepocket 28. Although the embodiment ofFIG. 2 includes onepocket hole 32, it is to be appreciated that two or more pocket holes 32 may be included. Thetab 30 includes at least onetab hole 36 extending therethrough and substantially aligned with the one or more pocket holes 32. While thetab hole 36 and thepocket hole 32 shown inFIG. 2 are round, it is to be appreciated that thetab hole 36 and/or thepocket hole 32 may be other shapes, for example oval or angular. - One or more retainers, for example, blade pins 38 are included to secure the
airfoil section 18 to theattachment section 20. Eachblade pin 38 extends tangentially through thepocket hole 32 and at least partially through thetab hole 36. Referring now toFIG. 3 , theblade pin 38 extends through thepocket hole 32 at afirst sidewall 34 of thepocket 28 and through thetab hole 36. In this embodiment, asecond sidewall 34 of the pocket is without apocket hole 32 so that atip 40 of theblade pin 38 does not pass entirely through thepocket 28. To prevent theblade pin 38 from being inadvertently removed, when theadjacent blade assembly 12 is installed in therotor 14, thesidewall 34 of theadjacent blade assembly 12 may substantially abut ahead 42 of theblade pin 38 to retain theblade pin 38 in theblade assembly 12. In other embodiments, the blade pin may be retained in theblade assembly 12 via a process such as welding, or other retention means. Further, theblade pin 38 may be assembled to theblade assembly 12 via a press fit. Even though ablade pin 38 is utilized in the illustrated embodiment ofFIG. 3 , it is to be appreciated that other means for securing theairfoil section 18 to theattachment section 20, including mechanical threaded fasteners, wedges, welding, and/or adhesives. - Referring again to
FIG. 2 , in some embodiments, theblade assembly 12 includes abushing 44 installed into the pocket holes 32 and tab holes 36 prior to installing theblade pin 38. Use of thebushing 44 reduces hertz stresses on theblade assembly 12 in the area of theblade pin 38. As shown inFIGS. 2 and 3 , asleeve 46, comprising for example, a relatively soft material, is disposed between thetab 30 and thepocket 28. Thesleeve 46 is utilized to reduce stresses and wear on thetab 30 and thepocket 28 at the interfaces between thetab 30 and thepocket 28. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (20)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/872,901 US20120051924A1 (en) | 2010-08-31 | 2010-08-31 | Turbine Blade Assembly |
DE102011050961A DE102011050961A1 (en) | 2010-08-31 | 2011-06-09 | Turbine blade arrangement |
CH01008/11A CH703775A2 (en) | 2010-08-31 | 2011-06-15 | Blade assembly for a rotor. |
JP2011141297A JP2012052523A (en) | 2010-08-31 | 2011-06-27 | Turbine blade assembly |
CN2011101923104A CN102383864A (en) | 2010-08-31 | 2011-06-30 | Turbine blade assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/872,901 US20120051924A1 (en) | 2010-08-31 | 2010-08-31 | Turbine Blade Assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
US20120051924A1 true US20120051924A1 (en) | 2012-03-01 |
Family
ID=45566316
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/872,901 Abandoned US20120051924A1 (en) | 2010-08-31 | 2010-08-31 | Turbine Blade Assembly |
Country Status (5)
Country | Link |
---|---|
US (1) | US20120051924A1 (en) |
JP (1) | JP2012052523A (en) |
CN (1) | CN102383864A (en) |
CH (1) | CH703775A2 (en) |
DE (1) | DE102011050961A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9664056B2 (en) | 2013-08-23 | 2017-05-30 | General Electric Company | Turbine system and adapter |
CN107023507A (en) * | 2017-05-25 | 2017-08-08 | 合肥皖化电泵有限公司 | Blade used in a kind of BCP impellers of pump |
FR3069572A1 (en) * | 2017-07-31 | 2019-02-01 | Safran Aircraft Engines | ROTOR DARK FOR AN AIRCRAFT TURBOMACHINE |
US10633985B2 (en) | 2012-06-25 | 2020-04-28 | General Electric Company | System having blade segment with curved mounting geometry |
US20200256204A1 (en) * | 2019-02-07 | 2020-08-13 | General Electric Company | Method for replacing metal airfoil with ceramic airfoil, and related turbomachine blade |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9435209B2 (en) * | 2012-10-25 | 2016-09-06 | General Electric Company | Turbomachine blade reinforcement |
CN113530607B (en) * | 2021-04-07 | 2022-07-05 | 西北工业大学 | Turbine blade disc with U-shaped blade pairs |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1959220A (en) * | 1933-05-26 | 1934-05-15 | Gen Electric | Rotary disk turbine bucket wheel, or the like |
US2840299A (en) * | 1952-09-22 | 1958-06-24 | Thompson Prod Inc | Axial flow compressor rotor |
US2980395A (en) * | 1953-04-10 | 1961-04-18 | Rolls Royce | Rotor with pivoted blades for compressors and turbines |
US3012308A (en) * | 1957-08-12 | 1961-12-12 | Joy Mfg Co | Method of making blade structures |
US3635587A (en) * | 1970-06-02 | 1972-01-18 | Gen Motors Corp | Blade cooling liner |
US3737250A (en) * | 1971-06-16 | 1973-06-05 | Us Navy | Fiber blade attachment |
US4008000A (en) * | 1974-08-28 | 1977-02-15 | Motoren-Und Turbinen-Union Munich Gmbh | Axial-flow rotor wheel for high-speed turbomachines |
US4361416A (en) * | 1979-04-14 | 1982-11-30 | Motoren- Und Turbinen-Union Munchen Gmbh | Rotor for axial-flow turbomachines |
US5464325A (en) * | 1993-06-25 | 1995-11-07 | Institut Fuer Luft- Und Kaeltetechnik Gemeinnuetzige Gesellschaft Mbh | Turbo-compressor impeller for coolant |
US20100189562A1 (en) * | 2009-01-28 | 2010-07-29 | Snecma | Composite material turbomachine blade with a reinforced root |
US20110142684A1 (en) * | 2009-12-15 | 2011-06-16 | Campbell Christian X | Turbine Engine Airfoil and Platform Assembly |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4767247A (en) * | 1987-02-24 | 1988-08-30 | Westinghouse Electric Corp. | Apparatus and method for preventing relative blade motion in steam turbine |
-
2010
- 2010-08-31 US US12/872,901 patent/US20120051924A1/en not_active Abandoned
-
2011
- 2011-06-09 DE DE102011050961A patent/DE102011050961A1/en not_active Withdrawn
- 2011-06-15 CH CH01008/11A patent/CH703775A2/en not_active Application Discontinuation
- 2011-06-27 JP JP2011141297A patent/JP2012052523A/en not_active Withdrawn
- 2011-06-30 CN CN2011101923104A patent/CN102383864A/en active Pending
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1959220A (en) * | 1933-05-26 | 1934-05-15 | Gen Electric | Rotary disk turbine bucket wheel, or the like |
US2840299A (en) * | 1952-09-22 | 1958-06-24 | Thompson Prod Inc | Axial flow compressor rotor |
US2980395A (en) * | 1953-04-10 | 1961-04-18 | Rolls Royce | Rotor with pivoted blades for compressors and turbines |
US3012308A (en) * | 1957-08-12 | 1961-12-12 | Joy Mfg Co | Method of making blade structures |
US3635587A (en) * | 1970-06-02 | 1972-01-18 | Gen Motors Corp | Blade cooling liner |
US3737250A (en) * | 1971-06-16 | 1973-06-05 | Us Navy | Fiber blade attachment |
US4008000A (en) * | 1974-08-28 | 1977-02-15 | Motoren-Und Turbinen-Union Munich Gmbh | Axial-flow rotor wheel for high-speed turbomachines |
US4361416A (en) * | 1979-04-14 | 1982-11-30 | Motoren- Und Turbinen-Union Munchen Gmbh | Rotor for axial-flow turbomachines |
US5464325A (en) * | 1993-06-25 | 1995-11-07 | Institut Fuer Luft- Und Kaeltetechnik Gemeinnuetzige Gesellschaft Mbh | Turbo-compressor impeller for coolant |
US20100189562A1 (en) * | 2009-01-28 | 2010-07-29 | Snecma | Composite material turbomachine blade with a reinforced root |
US20110142684A1 (en) * | 2009-12-15 | 2011-06-16 | Campbell Christian X | Turbine Engine Airfoil and Platform Assembly |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10633985B2 (en) | 2012-06-25 | 2020-04-28 | General Electric Company | System having blade segment with curved mounting geometry |
US9664056B2 (en) | 2013-08-23 | 2017-05-30 | General Electric Company | Turbine system and adapter |
CN107023507A (en) * | 2017-05-25 | 2017-08-08 | 合肥皖化电泵有限公司 | Blade used in a kind of BCP impellers of pump |
FR3069572A1 (en) * | 2017-07-31 | 2019-02-01 | Safran Aircraft Engines | ROTOR DARK FOR AN AIRCRAFT TURBOMACHINE |
US20200256204A1 (en) * | 2019-02-07 | 2020-08-13 | General Electric Company | Method for replacing metal airfoil with ceramic airfoil, and related turbomachine blade |
US10907484B2 (en) | 2019-02-07 | 2021-02-02 | General Electric Company | Method for replacing metal airfoil with ceramic airfoil, and related turbomachine blade |
US11480061B2 (en) | 2019-02-07 | 2022-10-25 | General Electric Company | Method for replacing metal airfoil with ceramic airfoil, and related turbomachine blade |
Also Published As
Publication number | Publication date |
---|---|
CH703775A2 (en) | 2012-03-15 |
JP2012052523A (en) | 2012-03-15 |
DE102011050961A1 (en) | 2012-03-01 |
CN102383864A (en) | 2012-03-21 |
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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:GARCIA-CRESPO, ANDRES JOSE;BRITTINGHAM, ROBERT ALAN;REEL/FRAME:024919/0822 Effective date: 20100827 |
|
AS | Assignment |
Owner name: ENERGY, UNITED STATES DEPARTMENT OF ENERGY, DISTRI Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:026980/0333 Effective date: 20110616 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |