GB201011325D0 - Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system - Google Patents

Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system

Info

Publication number
GB201011325D0
GB201011325D0 GBGB1011325.6A GB201011325A GB201011325D0 GB 201011325 D0 GB201011325 D0 GB 201011325D0 GB 201011325 A GB201011325 A GB 201011325A GB 201011325 D0 GB201011325 D0 GB 201011325D0
Authority
GB
United Kingdom
Prior art keywords
control system
compressor
gas turbine
turbine engine
blade tip
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.)
Withdrawn
Application number
GBGB1011325.6A
Other versions
GB2467893A (en
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
Publication of GB2467893A publication Critical patent/GB2467893A/en
Publication of GB201011325D0 publication Critical patent/GB201011325D0/en
Withdrawn legal-status Critical Current

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/687—Plasma actuators therefore
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • F05D2270/172—Purpose of the control system to control boundary layer by a plasma generator, e.g. control of ignition
GBGB1011325.6A 2007-12-28 2008-11-21 Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system Withdrawn GB201011325D0 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/966,309 US20100284795A1 (en) 2007-12-28 2007-12-28 Plasma Clearance Controlled Compressor
PCT/US2008/084315 WO2009085467A1 (en) 2007-12-28 2008-11-21 Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system

Publications (2)

Publication Number Publication Date
GB2467893A GB2467893A (en) 2010-08-18
GB201011325D0 true GB201011325D0 (en) 2010-08-18

Family

ID=40340572

Family Applications (1)

Application Number Title Priority Date Filing Date
GBGB1011325.6A Withdrawn GB201011325D0 (en) 2007-12-28 2008-11-21 Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system

Country Status (6)

Country Link
US (1) US20100284795A1 (en)
JP (1) JP2011508148A (en)
CA (1) CA2710376A1 (en)
DE (1) DE112008003506T5 (en)
GB (1) GB201011325D0 (en)
WO (1) WO2009085467A1 (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US8317457B2 (en) * 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
US20100047060A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Compressor
US20100284785A1 (en) * 2007-12-28 2010-11-11 Aspi Rustom Wadia Fan Stall Detection System
US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US8348592B2 (en) * 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
US20100290906A1 (en) * 2007-12-28 2010-11-18 Moeckel Curtis W Plasma sensor stall control system and turbomachinery diagnostics
US8282337B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US20100205928A1 (en) * 2007-12-28 2010-08-19 Moeckel Curtis W Rotor stall sensor system
US8282336B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US20090169356A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Compression System
US8096756B2 (en) * 2008-03-07 2012-01-17 Pratt & Whitney Canada Corp. Apparatus and method for controlling a compressor
US20100172747A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced compressor duct
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation
DE102009033754A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Axial compressor with a flow pulse generator
US9458855B2 (en) * 2010-12-30 2016-10-04 Rolls-Royce North American Technologies Inc. Compressor tip clearance control and gas turbine engine
DE102011007474B4 (en) * 2011-04-15 2012-11-15 Aktiebolaget Skf Sealing ring segment, sealing ring, seal, bearing and method for sealing a bearing gap
US9039346B2 (en) 2011-10-17 2015-05-26 General Electric Company Rotor support thermal control system
US20130251500A1 (en) * 2012-03-23 2013-09-26 Kin-Leung Cheung Gas turbine engine case with heating layer and method
GB201300597D0 (en) * 2012-10-22 2013-02-27 Rolls Royce Plc Clearance control
US10487679B2 (en) 2017-07-17 2019-11-26 United Technologies Corporation Method and apparatus for sealing components of a gas turbine engine with a dielectric barrier discharge plasma actuator
JP6674437B2 (en) * 2017-12-26 2020-04-01 株式会社Ｓｕｂａｒｕ Auxiliary device for rotor, rotor, gas turbine engine and aircraft

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2245316B (en) * 1990-06-21 1993-12-15 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
US6793455B2 (en) * 2001-02-08 2004-09-21 Georgia Tech Research Corporation Method and apparatus for active control of surge in compressors
US6871487B2 (en) * 2003-02-14 2005-03-29 Kulite Semiconductor Products, Inc. System for detecting and compensating for aerodynamic instabilities in turbo-jet engines
GB0411178D0 (en) * 2004-05-20 2004-06-23 Rolls Royce Plc Sealing arrangement
US7159401B1 (en) * 2004-12-23 2007-01-09 Kulite Semiconductor Products, Inc. System for detecting and compensating for aerodynamic instabilities in turbo-jet engines
JP5060163B2 (en) * 2006-04-28 2012-10-31 株式会社東芝 Wings
US7605595B2 (en) * 2006-09-29 2009-10-20 General Electric Company System for clearance measurement and method of operating the same
US7819626B2 (en) * 2006-10-13 2010-10-26 General Electric Company Plasma blade tip clearance control
US7766599B2 (en) * 2006-10-31 2010-08-03 General Electric Company Plasma lifted boundary layer gas turbine engine vane
US7588413B2 (en) * 2006-11-30 2009-09-15 General Electric Company Upstream plasma shielded film cooling
US7695241B2 (en) * 2006-11-30 2010-04-13 General Electric Company Downstream plasma shielded film cooling
US7736123B2 (en) * 2006-12-15 2010-06-15 General Electric Company Plasma induced virtual turbine airfoil trailing edge extension
US7628585B2 (en) * 2006-12-15 2009-12-08 General Electric Company Airfoil leading edge end wall vortex reducing plasma
WO2008154592A2 (en) * 2007-06-11 2008-12-18 University Of Florida Research Foundation, Inc. Electrodynamic control of blade clearance leakage loss in turbomachinery applications
US20090065064A1 (en) * 2007-08-02 2009-03-12 The University Of Notre Dame Du Lac Compressor tip gap flow control using plasma actuators
US8282336B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US20100047060A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Compressor
US8348592B2 (en) * 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US8282337B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US20090169356A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Compression System

Also Published As

Publication number Publication date
GB2467893A (en) 2010-08-18
US20100284795A1 (en) 2010-11-11
WO2009085467A8 (en) 2010-07-22
CA2710376A1 (en) 2009-07-09
DE112008003506T5 (en) 2010-11-04
WO2009085467A1 (en) 2009-07-09
JP2011508148A (en) 2011-03-10

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)