US20130170969A1 - Turbine Diffuser - Google Patents

Turbine Diffuser Download PDF

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Publication number
US20130170969A1
US20130170969A1 US13/343,021 US201213343021A US2013170969A1 US 20130170969 A1 US20130170969 A1 US 20130170969A1 US 201213343021 A US201213343021 A US 201213343021A US 2013170969 A1 US2013170969 A1 US 2013170969A1
Authority
US
United States
Prior art keywords
diffuser
airfoils
airfoil
hub
struts
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/343,021
Other languages
English (en)
Inventor
Moorthi Subramaniyan
Vignesh Radhakrishnan
Bala M. Singh
Manjunath B. C
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US13/343,021 priority Critical patent/US20130170969A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: C., MANJUNATH B., REDHAKRISHNAN, VIGNESH, SINGH, BALA M., Subramaniyan, Moorthi
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: RADHAKRISHNAN, VIGNESH, SINGH, BALA M., Subramaniyan, Moorthi, CHENGAPPA, MANJUNATH BANGALORE
Priority to EP12198699.6A priority patent/EP2740897A1/en
Priority to JP2012278796A priority patent/JP2013139785A/ja
Priority to RU2012158350/06A priority patent/RU2012158350A/ru
Priority to CN2013100012466A priority patent/CN103195572A/zh
Publication of US20130170969A1 publication Critical patent/US20130170969A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs

Definitions

  • the present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a turbine diffuser with an airfoil arrangement to reduce swirl and flow separation during partial load operations and the like.
  • Gas turbine engines and the like typically include a diffuser downstream of the last stage of a turbine.
  • the diffuser converts the kinetic energy of the hot flow gases exiting the last stage into potential energy in the form of increased static pressure.
  • the diffuser directs the hot flow gases through a casing of increasing area in the direction of the flow.
  • the diffuser generally includes a number of struts mounted onto a hub and enclosed by the casing. Other configurations also may be known.
  • a bucket exit tangential flow angle may increase and may lead to flow separation on the struts and the hub of the diffuser. Flow separation and an increase in swirl may reduce the diffuser static pressure recovery. Such a reduction may have an impact on overall gas turbine engine performance and efficiency.
  • Such an improved design preferably may limit flow separations and swirl so as to improve overall performance and efficiency.
  • the present application and the resultant patent thus provide a diffuser for use with a gas turbine.
  • the diffuser may include hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.
  • the present application and the resultant patent further provide a diffuser for use with a gas turbine.
  • the diffuser may include a hub, a number of struts extending from the hub, a number of airfoils extending from the hub such that one of the airfoils is positioned between a pair of the struts, and a casing.
  • the present application and the resultant patent further provide a diffuser for use with a gas turbine.
  • the diffuser may include a hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.
  • the airfoils may have a number of configurations.
  • FIG. 1 is a schematic diagram of a gas turbine engine showing a compressor, a combustor, a turbine, and a diffuser.
  • FIG. 2 is a partial perspective view of a portion of a diffuser as may be described herein.
  • FIG. 3 is a plan view of portions of the diffuser of FIG. 2
  • FIG. 4 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein.
  • FIG. 5 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein.
  • FIG. 6 is a plan view of portions of art alternative embodiment of a diffuser as may be described herein.
  • FIG. 7 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein.
  • FIG. 8 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein.
  • FIG. 9 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein.
  • FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 15 .
  • the compressor 15 compresses an incoming flow of air 20 .
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25 .
  • the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 .
  • the gas turbine engine 10 may include any number of combustors 25 .
  • the flow of combustion gases 35 is in turn delivered to a turbine 40 .
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • the gas turbine engine 10 also may include a diffuser 55 .
  • the diffuser 55 may be positioned downstream of the turbine 40 .
  • the diffuser 55 may include a number of struts 60 mounted on a hub 65 and enclosed within an outer casing 70 .
  • the diffuser 55 turns the flow of combustion gases 35 in an axial direction.
  • Other configurations and other components may be used.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • FIG. 2 and FIG. 3 show portions of an example of a diffuser 100 as may be described herein.
  • the diffuser 100 may include a number of struts 110 positioned on a hub 120 . Any number of struts 110 may be used.
  • the struts 110 and the hub 120 may have any size or shape.
  • the struts 110 may be enclosed within a casing that expands in diameter along the flow path therethrough. The casing may be similar to that described above. Other components and other configurations also may be used herein.
  • the diffuser 100 also may have a number of airfoils 130 positioned on the hub 120 .
  • the airfoils 130 may be positioned adjacent to the struts 110 .
  • an airfoil 130 may be positioned between each pair of the struts 110 .
  • Any number of the airfoils 130 may be used herein.
  • the angle, length, size, shape, and configuration of the airfoils 130 may vary. Airfoils 130 of different configurations may be used herein together.
  • a slot 140 may be positioned through a portion of the airfoil 130 .
  • the slot 140 serves to direct the flow of combustion gases 35 therethrough.
  • the slot 140 may have any desired size, shape, or configuration. Other components and other configurations may be used herein.
  • the use of the airfoils 130 thus corrects the creation of swirl and reduces flow separation about the struts 110 and the hub 120 of the diffuser 100 through the entire partial load operations. Moreover, the airfoils 130 may be designed to not incur additional losses during full load ISO and cold day operations. An increase in airfoil count/solidity reduces airfoil-strut pitch so as to correct the swirl and the flow separation.
  • the diffuser 100 thus may provide improved performance so as to improve overall gas turbine performance and efficiency.
  • the airfoil also may include additional features or mechanisms as shown in for example, FIGS. 4-9 . These additional features also avoid flow separation on the airfoil and improve performance.
  • FIG. 4 shows a diffuser 150 .
  • the diffuser 150 may include the strut 110 and a “hunch back”-like airfoil 160 positioned adjacent thereto.
  • the hunch back airfoil 160 may have a spoiler like configuration 165 to direct the flow of combustion gases 35 .
  • FIG. 5 shows a further example of a diffuser 170 .
  • the diffuser 170 may include the strut 110 and a vortex generator airfoil 180 positioned adjacent thereto.
  • the vortex generator airfoil 180 may have a largely sinusoidal configuration 185 to direct the flow of combustion gases 35 .
  • FIG. 6 shows a further example of a diffuser 190 .
  • the diffuser 190 may include the strut 110 and a fluidic airfoil 200 positioned adjacent thereto.
  • the fluidic airfoil 200 may have a number of fluidic ports 210 to provide suction and/or blowing so as to direct the flow of combustion gases 35 .
  • FIG. 7 shows a further example of a diffuser 220 .
  • the diffuser 220 may include the strut 110 and a high lift airfoil 230 positioned adjacent thereto.
  • the high lift airfoil 230 may include a number of airfoil elements 240 so as to direct the flow of combustion gases 35 .
  • FIG. 8 shows a further example of a diffuser 250 .
  • the diffuser 250 may include the strut 110 and a cambered airfoil 260 positioned adjacent thereto.
  • the cambered airfoil 260 may take a thickened configuration 270 so as to direct the flow of combustion gases 35 .
  • FIG. 9 shows a further example of a diffuser 250 .
  • the diffuser 250 may include the strut 110 and an extended airfoil 280 positioned adjacent thereto.
  • the extended airfoil 280 may take a forward bend 290 so as to direct the flow of combustion gases 35 .
  • the diffusers described herein thus may elude airfoils 130 of various sizes, shapes, and configurations.
  • the use of the airfoils 130 with the struts 110 thus controls the flow separation and swirl during partial load operations so as to improve overall efficiency.
  • Many other sizes, shapes, and configurations of diffusers and airfoils may be used herein.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/343,021 2012-01-04 2012-01-04 Turbine Diffuser Abandoned US20130170969A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/343,021 US20130170969A1 (en) 2012-01-04 2012-01-04 Turbine Diffuser
EP12198699.6A EP2740897A1 (en) 2012-01-04 2012-12-20 Turbine diffuser
JP2012278796A JP2013139785A (ja) 2012-01-04 2012-12-21 タービンディフューザ
RU2012158350/06A RU2012158350A (ru) 2012-01-04 2012-12-27 Диффузор для газовой турбины (варианты)
CN2013100012466A CN103195572A (zh) 2012-01-04 2013-01-04 涡轮扩散器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/343,021 US20130170969A1 (en) 2012-01-04 2012-01-04 Turbine Diffuser

Publications (1)

Publication Number Publication Date
US20130170969A1 true US20130170969A1 (en) 2013-07-04

Family

ID=47664077

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/343,021 Abandoned US20130170969A1 (en) 2012-01-04 2012-01-04 Turbine Diffuser

Country Status (5)

Country Link
US (1) US20130170969A1 (ja)
EP (1) EP2740897A1 (ja)
JP (1) JP2013139785A (ja)
CN (1) CN103195572A (ja)
RU (1) RU2012158350A (ja)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015142200A1 (en) 2014-03-18 2015-09-24 General Electric Company Exhaust gas diffuser with main struts and small struts
US20160348537A1 (en) * 2015-05-29 2016-12-01 Siemens Energy, Inc. Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction
GB2568109A (en) * 2017-11-07 2019-05-08 Gkn Aerospace Sweden Ab Splitter vane
US10563543B2 (en) 2016-05-31 2020-02-18 General Electric Company Exhaust diffuser
US11371370B2 (en) 2017-07-19 2022-06-28 MTU Aero Engines AG Flow arrangement for placing in a hot gas duct of a turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9836066B2 (en) * 2014-07-16 2017-12-05 Caterpillar Inc. Vortex diffuser for rotating/stationary interfaces
JP2016217355A (ja) 2015-05-22 2016-12-22 ゼネラル・エレクトリック・カンパニイ 流れ混合ローブを含むターボ機械ディフューザ及びその方法

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US2938336A (en) * 1956-12-06 1960-05-31 United Aircraft Corp Gas flow straightening vanes
US2941781A (en) * 1955-10-13 1960-06-21 Westinghouse Electric Corp Guide vane array for turbines
US3299632A (en) * 1964-05-08 1967-01-24 Rolls Royce Combustion chamber for a gas turbine engine
US3704075A (en) * 1970-12-14 1972-11-28 Caterpillar Tractor Co Combined turbine nozzle and bearing frame
US4624104A (en) * 1984-05-15 1986-11-25 A/S Kongsberg Vapenfabrikk Variable flow gas turbine engine
US4793770A (en) * 1987-08-06 1988-12-27 General Electric Company Gas turbine engine frame assembly
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US6139259A (en) * 1998-10-29 2000-10-31 General Electric Company Low noise permeable airfoil
US6435815B2 (en) * 2000-01-22 2002-08-20 Rolls-Royce Plc Aerofoil for an axial flow turbo machine
US6715983B2 (en) * 2001-09-27 2004-04-06 General Electric Company Method and apparatus for reducing distortion losses induced to gas turbine engine airflow
US20040228726A1 (en) * 2003-05-16 2004-11-18 Kouichi Ishizaka Exhaust diffuser for axial-flow turbine
WO2005040559A1 (en) * 2003-10-17 2005-05-06 Paolo Pietricola High lift rotor or stator blades with multiple adjacent airfoils cross-section
US6997676B2 (en) * 2004-03-10 2006-02-14 General Electric Company Bifurcated outlet guide vanes
US7195456B2 (en) * 2004-12-21 2007-03-27 United Technologies Corporation Turbine engine guide vane and arrays thereof
JP2009215897A (ja) * 2008-03-07 2009-09-24 Mitsubishi Heavy Ind Ltd ガスタービンエンジン
WO2010009707A2 (de) * 2008-07-19 2010-01-28 Mtu Aero Engines Gmbh Schaufel einer strömungsmaschine mit vortex-generator
US20100158684A1 (en) * 2006-11-14 2010-06-24 Baralon Stephane Vane assembly configured for turning a flow in a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
US20100272566A1 (en) * 2009-04-24 2010-10-28 Pratt & Whitney Canada Corp. Deflector for a gas turbine strut and vane assembly
US7824152B2 (en) * 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
US8257036B2 (en) * 2004-04-09 2012-09-04 Norris Thomas R Externally mounted vortex generators for flow duct passage
US20140096500A1 (en) * 2012-10-05 2014-04-10 General Electric Company Exhaust diffuser
US20140137533A1 (en) * 2012-11-19 2014-05-22 General Electric Company Exhaust gas diffuser for a gas turbine
US20140161603A1 (en) * 2012-12-07 2014-06-12 General Electric Company Exhaust diffuser
US20140178187A1 (en) * 2012-12-20 2014-06-26 General Electric Company Staggered double row, slotted airfoil design for gas turbine exhaust frame

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US2314572A (en) * 1938-12-07 1943-03-23 Herman E Chitz Turboengine
US4023350A (en) * 1975-11-10 1977-05-17 United Technologies Corporation Exhaust case for a turbine machine
EP0978632A1 (de) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomaschine mit Zwischenschaufeln als Strömungsteilelemente
US20110052373A1 (en) * 2009-09-03 2011-03-03 General Electric Company High-turning diffuser strut with flow cross-over slots

Patent Citations (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941781A (en) * 1955-10-13 1960-06-21 Westinghouse Electric Corp Guide vane array for turbines
US2938336A (en) * 1956-12-06 1960-05-31 United Aircraft Corp Gas flow straightening vanes
US3299632A (en) * 1964-05-08 1967-01-24 Rolls Royce Combustion chamber for a gas turbine engine
US3704075A (en) * 1970-12-14 1972-11-28 Caterpillar Tractor Co Combined turbine nozzle and bearing frame
US4624104A (en) * 1984-05-15 1986-11-25 A/S Kongsberg Vapenfabrikk Variable flow gas turbine engine
US4793770A (en) * 1987-08-06 1988-12-27 General Electric Company Gas turbine engine frame assembly
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US6139259A (en) * 1998-10-29 2000-10-31 General Electric Company Low noise permeable airfoil
US6435815B2 (en) * 2000-01-22 2002-08-20 Rolls-Royce Plc Aerofoil for an axial flow turbo machine
US6715983B2 (en) * 2001-09-27 2004-04-06 General Electric Company Method and apparatus for reducing distortion losses induced to gas turbine engine airflow
US20040228726A1 (en) * 2003-05-16 2004-11-18 Kouichi Ishizaka Exhaust diffuser for axial-flow turbine
WO2005040559A1 (en) * 2003-10-17 2005-05-06 Paolo Pietricola High lift rotor or stator blades with multiple adjacent airfoils cross-section
US6997676B2 (en) * 2004-03-10 2006-02-14 General Electric Company Bifurcated outlet guide vanes
US8257036B2 (en) * 2004-04-09 2012-09-04 Norris Thomas R Externally mounted vortex generators for flow duct passage
US7195456B2 (en) * 2004-12-21 2007-03-27 United Technologies Corporation Turbine engine guide vane and arrays thereof
US20100158684A1 (en) * 2006-11-14 2010-06-24 Baralon Stephane Vane assembly configured for turning a flow in a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine
US7824152B2 (en) * 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
JP2009215897A (ja) * 2008-03-07 2009-09-24 Mitsubishi Heavy Ind Ltd ガスタービンエンジン
WO2010009707A2 (de) * 2008-07-19 2010-01-28 Mtu Aero Engines Gmbh Schaufel einer strömungsmaschine mit vortex-generator
US8814529B2 (en) * 2008-07-19 2014-08-26 Mtu Aero Engines Gmbh Blade for a turbo device with a vortex-generator
US20100272566A1 (en) * 2009-04-24 2010-10-28 Pratt & Whitney Canada Corp. Deflector for a gas turbine strut and vane assembly
US20140096500A1 (en) * 2012-10-05 2014-04-10 General Electric Company Exhaust diffuser
US20140137533A1 (en) * 2012-11-19 2014-05-22 General Electric Company Exhaust gas diffuser for a gas turbine
US20140161603A1 (en) * 2012-12-07 2014-06-12 General Electric Company Exhaust diffuser
US20140178187A1 (en) * 2012-12-20 2014-06-26 General Electric Company Staggered double row, slotted airfoil design for gas turbine exhaust frame

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015142200A1 (en) 2014-03-18 2015-09-24 General Electric Company Exhaust gas diffuser with main struts and small struts
US10392975B2 (en) 2014-03-18 2019-08-27 General Electric Company Exhaust gas diffuser with main struts and small struts
US20160348537A1 (en) * 2015-05-29 2016-12-01 Siemens Energy, Inc. Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction
US10047636B2 (en) * 2015-05-29 2018-08-14 Siemens Energy, Inc. Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction
US10563543B2 (en) 2016-05-31 2020-02-18 General Electric Company Exhaust diffuser
US11371370B2 (en) 2017-07-19 2022-06-28 MTU Aero Engines AG Flow arrangement for placing in a hot gas duct of a turbomachine
GB2568109A (en) * 2017-11-07 2019-05-08 Gkn Aerospace Sweden Ab Splitter vane
GB2568109B (en) * 2017-11-07 2021-06-09 Gkn Aerospace Sweden Ab Splitter vane

Also Published As

Publication number Publication date
JP2013139785A (ja) 2013-07-18
CN103195572A (zh) 2013-07-10
RU2012158350A (ru) 2014-07-10
EP2740897A1 (en) 2014-06-11

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SUBRAMANIYAN, MOORTHI;REDHAKRISHNAN, VIGNESH;SINGH, BALA M.;AND OTHERS;REEL/FRAME:027474/0420

Effective date: 20111102

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SUBRAMANIYAN, MOORTHI;RADHAKRISHNAN, VIGNESH;SINGH, BALA M.;AND OTHERS;SIGNING DATES FROM 20121115 TO 20121127;REEL/FRAME:029396/0301

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION