US20130022444A1 - Low pressure turbine exhaust diffuser with turbulators - Google Patents
Low pressure turbine exhaust diffuser with turbulators Download PDFInfo
- Publication number
- US20130022444A1 US20130022444A1 US13/185,861 US201113185861A US2013022444A1 US 20130022444 A1 US20130022444 A1 US 20130022444A1 US 201113185861 A US201113185861 A US 201113185861A US 2013022444 A1 US2013022444 A1 US 2013022444A1
- Authority
- US
- United States
- Prior art keywords
- diffuser
- turbulators
- turbine exhaust
- inlet
- exhaust diffuser
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
Definitions
- This invention relates to steam turbine technology in general, and to an axial-to-radial flow, low pressure, steam turbine exhaust gas diffuser in particular.
- a steam turbine low pressure (LP) section typically includes an inlet domain, multiple turbine stages and an exhaust gas diffuser (sometimes referenced to as an exhaust hood).
- the exhaust gas diffuser is typically located at the last row of rotating blades or buckets, and is formed to include a steam flow guide between an axial flow inlet and a radial flow outlet. Flow diffusion takes place in the initial section of the diffuser, formed by the diffuser steam flow guide while the remainder of the diffuser features collect the gas flow in a chamber and guide it to the condenser.
- diffuser or exhaust hood One of the main functions of the diffuser or exhaust hood is to recover static pressure as it guides the exhaust gas flow from the last stage row of buckets into the condenser.
- diffusers are typically designed with respect to optimized turbine performance which may be measured in terms of maximum possible static pressure recovery.
- the degree of static pressure recovery in the low pressure exhaust diffuser depends to a large extent on the Area Ratio formed by steam guide profile and on the last stage bucket exit profile, including bucket tip clearance. Generally, maximum pressure recovery comes at the end of the steam guide, but after that, pressure losses occur due to improper area scheduling.
- the invention provides a turbine exhaust diffuser for use adjacent a last stage row of buckets fixed to a turbine rotor comprising an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet; the outer diffuser ring having a curved steam guide surface extending between the diffuser inlet and the diffuser outlet and having a first portion extending away from the diffuser inlet and a second portion, extending to the diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction; wherein the second portion is provided with a plurality of turbulators.
- a turbine exhaust diffuser adjacent a last stage row of buckets fixed to a turbine rotor comprising an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet;
- the outer diffuser ring having a curved steam guide surface extending between the diffuser inlet and the diffuser outlet and having a first portion extending away from the diffuser inlet and a second portion extending to the diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction; wherein the second portion is provided with a plurality of turbulators arranged in at least two radially-spaced, circumferential rows.
- a method of method of increasing an outlet area of a turbine exhaust diffuser and minimizing flow separation along an outer wall portion of said turbine exhaust diffuser comprising shaping the outer wall portion extending between an axially-oriented diffuser inlet to a substantially radially oriented diffuser outlet to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in an upstream direction; and providing plural turbulators on the outer wall portion to generate localized vortices to minimize flow separation along the outer wall portion.
- FIG. 1 is a cross section through an upper or radially outer portion of a gas turbine exhaust diffuser in accordance with an exemplary but nonlimiting embodiment of the invention
- FIG. 2 is a perspective view of the diffuser portion shown in FIG. 1 ;
- FIG. 3 is an enlarged detail taken from FIG. 2 ;
- FIG. 4 illustrates the degree of flow separation in an example diffuser in accordance with the invention, but without turbulators or vortex generators;
- FIG. 5 illustrates a diffuser as shown in FIG. 4 but illustrating a reduction in flow separation achieved with the addition of turbulators or vortex generators in accordance with the invention.
- FIG. 1 there is shown a radially outer portion of an exhaust hood or diffuser 10 that may be part of a low pressure steam turbine.
- the diffuser 10 guides the turbine engine exhaust flow from the last stage blades or buckets 12 into an exhaust steam housing (not shown) and then to a condenser (also, not shown).
- the diffuser is generally shaped as a hollow toroid, with only a profile or cross section of the radially outer portion of the diffuser shown in FIG. 1 .
- the diffuser 10 is generally formed by an outer ring 14 and an inner ring 16 that are joined to create the hollow toroidal shape, with an inlet 18 to the diffuser 10 closely adjacent the last row of blades or buckets, represented by the single blade 12 .
- the diffuser 10 thus forms a steam guide or flow path for steam exiting the last stage row of blades or buckets that extends initially in a substantially axial direction at the last stage 12 and then turns substantially ninety degrees, terminating at the diffuser outlet 20 .
- an outer ring portion (also referred to as the steam guide portion) of a conventional diffuser closest to the blade tips extends substantially vertically, i.e., substantially perpendicular to the turbine rotor axis (that extends substantially parallel to the diffuser surface 23 ).
- This steam guide portion of the diffuser is shown at 22 in dotted line-format in FIG. 1 .
- both the inner and outer rings are substantially vertically-oriented.
- the area ratio at the outlet 20 , along diffuser steam guide wall portion or surface 24 is increased by turning the inner ring beyond vertical, back toward the turbine exit stage, thus providing a flow component in a second axial or upstream direction, e.g., by about 15° (See FIG. 1 and compare the dotted line 22 with the solid line 24 ).
- this approach has a tendency to cause undesirable boundary layer separation along the steam guide wall surface 24 , particularly that portion closest to the outlet 20 , as shown in FIG. 4 .
- turbulators or vortex generators 26 are disclosed as hemispherical projections with two, radially-spaced, circumferential rows arranged about the inner ring 14 , specifically about that portion of steam guide wall surface 24 that is shaped to extend beyond vertical and back toward the last stage buckets. It will be appreciated, however, that the invention is not limited to turbulators or vortex generators of hemispherical shape, but also contemplates hemispherical dimples or recesses.
- the shape may also vary from round to oval to rectangular, etc. and the height or depth may also vary as will be appreciated by those skilled in the art. It is also within the scope of the invention to vary the number of rows of turbulators or vortex generators, and to have the turbulators or vortex generators in adjacent rows circumferentially aligned with, or staggered relative to adjacent rows.
- turbulators or vortex generators 26 on the inside surface 24 of the diffuser outlet has been shown to increase pressure recovery to a significant degree.
- the turbulators or vortex generators 26 energize the boundary layer due to increased turbulence or localized vortices, helping to keep the flow attached to the surface 24 and thus increasing the static pressure recovery.
- the pressure recovery improved by a factor of 0.07 (where 100% pressure recovery is given a value of 1.0, the pressure recovery improved from 0.64 to 0.71). This difference is illustrated diagrammatically in FIGS. 4 and 5 with flow separation indicated by cross-hatching along the steam guide surface 24 .
- the invention provides for highly effective flow diffusion which yields a reduction of the so-called backpressure for the turbine, allowing the turbine to have an increased overall pressure ratio for the same temperature reservoir of the thermodynamiccycle, or to deliver the same output at a higher efficiency (i.e., for a reduced fuel input).
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/185,861 US20130022444A1 (en) | 2011-07-19 | 2011-07-19 | Low pressure turbine exhaust diffuser with turbulators |
DE102012106397A DE102012106397A1 (de) | 2011-07-19 | 2012-07-16 | Niederdruckturbinenauslassdiffusor mit Turbulatoren |
FR1256846A FR2978200A1 (fr) | 2011-07-19 | 2012-07-16 | Diffuseur d'echappement de turbine basse pression avec turbulateurs |
RU2012130316/06A RU2012130316A (ru) | 2011-07-19 | 2012-07-18 | Выхлопной диффузор турбины (варианты) и способ увеличения площади выходного отверстия выпускного диффузора и сведения к минимуму отрыва потока вдоль части наружной стенки выпускного диффузора |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/185,861 US20130022444A1 (en) | 2011-07-19 | 2011-07-19 | Low pressure turbine exhaust diffuser with turbulators |
Publications (1)
Publication Number | Publication Date |
---|---|
US20130022444A1 true US20130022444A1 (en) | 2013-01-24 |
Family
ID=47469720
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/185,861 Abandoned US20130022444A1 (en) | 2011-07-19 | 2011-07-19 | Low pressure turbine exhaust diffuser with turbulators |
Country Status (4)
Country | Link |
---|---|
US (1) | US20130022444A1 (ru) |
DE (1) | DE102012106397A1 (ru) |
FR (1) | FR2978200A1 (ru) |
RU (1) | RU2012130316A (ru) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109139255A (zh) * | 2017-06-19 | 2019-01-04 | 通用电气波兰有限责任公司 | 具有涡流发生器的排气组件及其排气方法 |
US11143058B2 (en) | 2017-12-20 | 2021-10-12 | General Electric Company | Exhaust device and an associated method thereof |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3023322B1 (fr) * | 2014-07-03 | 2019-09-06 | Safran Aircraft Engines | Manche d'entree d'air pour turbomachine |
Citations (43)
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---|---|---|---|---|
US2615301A (en) * | 1946-11-09 | 1952-10-28 | United Aircraft Corp | Centrifugal diffuser |
US2674845A (en) * | 1951-05-02 | 1954-04-13 | Walter D Pouchot | Diffuser apparatus with boundary layer control |
US2724545A (en) * | 1949-12-05 | 1955-11-22 | Tech Studien Ag | Discharge casings for axial flow engines |
US3144202A (en) * | 1960-11-19 | 1964-08-11 | Helmbold Theodor | Stabilizing devices for generating and guiding potential whirls |
US3149470A (en) * | 1962-08-29 | 1964-09-22 | Gen Electric | Low pressure turbine exhaust hood |
US3552877A (en) * | 1968-02-15 | 1971-01-05 | Escher Wyss Ltd | Outlet housing for an axial-flow turbomachine |
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US4182595A (en) * | 1978-01-30 | 1980-01-08 | Westinghouse Electric Corp. | Discharge assembly for an axial flow compressor |
US4214452A (en) * | 1977-08-25 | 1980-07-29 | Alsthom-Atlantique | Exhaust device for a condensable-fluid axial-flow turbine |
US4315715A (en) * | 1978-07-26 | 1982-02-16 | Nissan Motor Company, Limited | Diffuser for fluid impelling device |
US4971768A (en) * | 1987-11-23 | 1990-11-20 | United Technologies Corporation | Diffuser with convoluted vortex generator |
US5110560A (en) * | 1987-11-23 | 1992-05-05 | United Technologies Corporation | Convoluted diffuser |
US5203674A (en) * | 1982-11-23 | 1993-04-20 | Nuovo Pignone S.P.A. | Compact diffuser, particularly suitable for high-power gas turbines |
US5361828A (en) * | 1993-02-17 | 1994-11-08 | General Electric Company | Scaled heat transfer surface with protruding ramp surface turbulators |
US5536146A (en) * | 1989-02-03 | 1996-07-16 | Hitachi, Ltd. | Combined generator system |
US5547339A (en) * | 1995-04-11 | 1996-08-20 | Comair Rotron, Inc. | Turbulator for a fluid impelling device |
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US6439840B1 (en) * | 2000-11-30 | 2002-08-27 | Pratt & Whitney Canada Corp. | Bypass duct fan noise reduction assembly |
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US6589600B1 (en) * | 1999-06-30 | 2003-07-08 | General Electric Company | Turbine engine component having enhanced heat transfer characteristics and method for forming same |
US6598781B2 (en) * | 1999-05-03 | 2003-07-29 | General Electric Company | Article having turbulation and method of providing turbulation on an article |
US6602046B2 (en) * | 1999-02-15 | 2003-08-05 | Universität Stuttgart | Diffusor without any pulsation of the shock boundary layer, and a method for suppressing the shock boundary layer pulsation in diffusors |
US20040052643A1 (en) * | 2002-09-18 | 2004-03-18 | Bunker Ronald Scott | Linear surface concavity enhancement |
US20040091350A1 (en) * | 2002-11-13 | 2004-05-13 | Paolo Graziosi | Fluidic actuation for improved diffuser performance |
US7104067B2 (en) * | 2002-10-24 | 2006-09-12 | General Electric Company | Combustor liner with inverted turbulators |
US20080104961A1 (en) * | 2006-11-08 | 2008-05-08 | Ronald Scott Bunker | Method and apparatus for enhanced mixing in premixing devices |
US20080315012A1 (en) * | 2002-06-21 | 2008-12-25 | Darko Segota | Method and System for Regulating Internal Fluid Flow Within an Enclosed or Semi-enclosed Environment |
US20090263241A1 (en) * | 2006-11-13 | 2009-10-22 | Alstom Technology Ltd | Diffuser and exhaust system for turbine |
US20090308075A1 (en) * | 2005-03-31 | 2009-12-17 | Hitachi, Ltd. | Turbine exhaust system and method for modifying the same |
US20100034647A1 (en) * | 2006-12-07 | 2010-02-11 | General Electric Company | Processes for the formation of positive features on shroud components, and related articles |
US7731475B2 (en) * | 2007-05-17 | 2010-06-08 | Elliott Company | Tilted cone diffuser for use with an exhaust system of a turbine |
US20100172747A1 (en) * | 2009-01-08 | 2010-07-08 | General Electric Company | Plasma enhanced compressor duct |
US7780403B2 (en) * | 2006-09-08 | 2010-08-24 | Siemens Energy, Inc. | Adjustable turbine exhaust flow guide and bearing cone assemblies |
US20100260598A1 (en) * | 2009-04-08 | 2010-10-14 | Rolls-Royce Plc | Thermal control system for turbines |
US20110164972A1 (en) * | 2010-01-04 | 2011-07-07 | General Electric Company | Hollow steam guide diffuser having increased pressure recovery |
US20120034064A1 (en) * | 2010-08-06 | 2012-02-09 | General Electric Company | Contoured axial-radial exhaust diffuser |
US20120121405A1 (en) * | 2010-11-16 | 2012-05-17 | General Electric Company | Low pressure exhaust gas diffuser for a steam turbine |
US20120171030A1 (en) * | 2009-09-16 | 2012-07-05 | Mitsubishi Heavy Industries, Ltd. | Discharge scroll and turbomachine |
US8221054B2 (en) * | 2009-05-28 | 2012-07-17 | General Electric Company | Corrugated hood for low pressure steam turbine |
US8337160B2 (en) * | 2009-10-19 | 2012-12-25 | Toyota Motor Engineering & Manufacturing North America, Inc. | High efficiency turbine system |
US20130019583A1 (en) * | 2011-07-22 | 2013-01-24 | Kin Pong Lo | Diffuser with backward facing step having varying step height |
US8475125B2 (en) * | 2010-04-13 | 2013-07-02 | General Electric Company | Shroud vortex remover |
-
2011
- 2011-07-19 US US13/185,861 patent/US20130022444A1/en not_active Abandoned
-
2012
- 2012-07-16 DE DE102012106397A patent/DE102012106397A1/de not_active Withdrawn
- 2012-07-16 FR FR1256846A patent/FR2978200A1/fr not_active Withdrawn
- 2012-07-18 RU RU2012130316/06A patent/RU2012130316A/ru not_active Application Discontinuation
Patent Citations (47)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2615301A (en) * | 1946-11-09 | 1952-10-28 | United Aircraft Corp | Centrifugal diffuser |
US2724545A (en) * | 1949-12-05 | 1955-11-22 | Tech Studien Ag | Discharge casings for axial flow engines |
US2674845A (en) * | 1951-05-02 | 1954-04-13 | Walter D Pouchot | Diffuser apparatus with boundary layer control |
US3144202A (en) * | 1960-11-19 | 1964-08-11 | Helmbold Theodor | Stabilizing devices for generating and guiding potential whirls |
US3149470A (en) * | 1962-08-29 | 1964-09-22 | Gen Electric | Low pressure turbine exhaust hood |
US3552877A (en) * | 1968-02-15 | 1971-01-05 | Escher Wyss Ltd | Outlet housing for an axial-flow turbomachine |
US3578264A (en) * | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3578264B1 (ru) * | 1968-07-09 | 1991-11-19 | Univ Michigan | |
US4214452A (en) * | 1977-08-25 | 1980-07-29 | Alsthom-Atlantique | Exhaust device for a condensable-fluid axial-flow turbine |
US4182595A (en) * | 1978-01-30 | 1980-01-08 | Westinghouse Electric Corp. | Discharge assembly for an axial flow compressor |
US4315715A (en) * | 1978-07-26 | 1982-02-16 | Nissan Motor Company, Limited | Diffuser for fluid impelling device |
US5203674A (en) * | 1982-11-23 | 1993-04-20 | Nuovo Pignone S.P.A. | Compact diffuser, particularly suitable for high-power gas turbines |
US4971768A (en) * | 1987-11-23 | 1990-11-20 | United Technologies Corporation | Diffuser with convoluted vortex generator |
US5110560A (en) * | 1987-11-23 | 1992-05-05 | United Technologies Corporation | Convoluted diffuser |
US5536146A (en) * | 1989-02-03 | 1996-07-16 | Hitachi, Ltd. | Combined generator system |
US5361828A (en) * | 1993-02-17 | 1994-11-08 | General Electric Company | Scaled heat transfer surface with protruding ramp surface turbulators |
US5547339A (en) * | 1995-04-11 | 1996-08-20 | Comair Rotron, Inc. | Turbulator for a fluid impelling device |
US5737915A (en) * | 1996-02-09 | 1998-04-14 | General Electric Co. | Tri-passage diffuser for a gas turbine |
US6602046B2 (en) * | 1999-02-15 | 2003-08-05 | Universität Stuttgart | Diffusor without any pulsation of the shock boundary layer, and a method for suppressing the shock boundary layer pulsation in diffusors |
US6598781B2 (en) * | 1999-05-03 | 2003-07-29 | General Electric Company | Article having turbulation and method of providing turbulation on an article |
US6589600B1 (en) * | 1999-06-30 | 2003-07-08 | General Electric Company | Turbine engine component having enhanced heat transfer characteristics and method for forming same |
US20020025248A1 (en) * | 1999-08-16 | 2002-02-28 | Ching-Pang Lee | Method for enhancing heat transfer inside a turbulated cooling passage |
US6533546B2 (en) * | 2000-07-31 | 2003-03-18 | Alstom (Switzerland) Ltd. | Low-pressure steam turbine with multi-channel diffuser |
US6439840B1 (en) * | 2000-11-30 | 2002-08-27 | Pratt & Whitney Canada Corp. | Bypass duct fan noise reduction assembly |
US20080315012A1 (en) * | 2002-06-21 | 2008-12-25 | Darko Segota | Method and System for Regulating Internal Fluid Flow Within an Enclosed or Semi-enclosed Environment |
US20040052643A1 (en) * | 2002-09-18 | 2004-03-18 | Bunker Ronald Scott | Linear surface concavity enhancement |
US7104067B2 (en) * | 2002-10-24 | 2006-09-12 | General Electric Company | Combustor liner with inverted turbulators |
US20040091350A1 (en) * | 2002-11-13 | 2004-05-13 | Paolo Graziosi | Fluidic actuation for improved diffuser performance |
US20090308075A1 (en) * | 2005-03-31 | 2009-12-17 | Hitachi, Ltd. | Turbine exhaust system and method for modifying the same |
US7780403B2 (en) * | 2006-09-08 | 2010-08-24 | Siemens Energy, Inc. | Adjustable turbine exhaust flow guide and bearing cone assemblies |
US20080104961A1 (en) * | 2006-11-08 | 2008-05-08 | Ronald Scott Bunker | Method and apparatus for enhanced mixing in premixing devices |
US20090263241A1 (en) * | 2006-11-13 | 2009-10-22 | Alstom Technology Ltd | Diffuser and exhaust system for turbine |
US7934904B2 (en) * | 2006-11-13 | 2011-05-03 | Alstom Technology Ltd. | Diffuser and exhaust system for turbine |
US20100034647A1 (en) * | 2006-12-07 | 2010-02-11 | General Electric Company | Processes for the formation of positive features on shroud components, and related articles |
US7731475B2 (en) * | 2007-05-17 | 2010-06-08 | Elliott Company | Tilted cone diffuser for use with an exhaust system of a turbine |
US20100172747A1 (en) * | 2009-01-08 | 2010-07-08 | General Electric Company | Plasma enhanced compressor duct |
US20100260598A1 (en) * | 2009-04-08 | 2010-10-14 | Rolls-Royce Plc | Thermal control system for turbines |
US8221054B2 (en) * | 2009-05-28 | 2012-07-17 | General Electric Company | Corrugated hood for low pressure steam turbine |
US20120171030A1 (en) * | 2009-09-16 | 2012-07-05 | Mitsubishi Heavy Industries, Ltd. | Discharge scroll and turbomachine |
US8337160B2 (en) * | 2009-10-19 | 2012-12-25 | Toyota Motor Engineering & Manufacturing North America, Inc. | High efficiency turbine system |
US20110164972A1 (en) * | 2010-01-04 | 2011-07-07 | General Electric Company | Hollow steam guide diffuser having increased pressure recovery |
US8439633B2 (en) * | 2010-01-04 | 2013-05-14 | General Electric Company | Hollow steam guide diffuser having increased pressure recovery |
US8475125B2 (en) * | 2010-04-13 | 2013-07-02 | General Electric Company | Shroud vortex remover |
US20120034064A1 (en) * | 2010-08-06 | 2012-02-09 | General Electric Company | Contoured axial-radial exhaust diffuser |
US20120121405A1 (en) * | 2010-11-16 | 2012-05-17 | General Electric Company | Low pressure exhaust gas diffuser for a steam turbine |
US8591185B2 (en) * | 2010-11-16 | 2013-11-26 | General Electric Company | Low pressure exhaust gas diffuser for a steam turbine |
US20130019583A1 (en) * | 2011-07-22 | 2013-01-24 | Kin Pong Lo | Diffuser with backward facing step having varying step height |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109139255A (zh) * | 2017-06-19 | 2019-01-04 | 通用电气波兰有限责任公司 | 具有涡流发生器的排气组件及其排气方法 |
US11143058B2 (en) | 2017-12-20 | 2021-10-12 | General Electric Company | Exhaust device and an associated method thereof |
Also Published As
Publication number | Publication date |
---|---|
DE102012106397A1 (de) | 2013-01-31 |
FR2978200A1 (fr) | 2013-01-25 |
RU2012130316A (ru) | 2014-01-27 |
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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:NEELI, SUDHAKAR;JOHN, JOSHY;BARB, KEVIN JOSEPH;SIGNING DATES FROM 20110629 TO 20110630;REEL/FRAME:026614/0098 |
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STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |