WO2009085467A8 - 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 Download PDF

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Publication number
WO2009085467A8
WO2009085467A8 PCT/US2008/084315 US2008084315W WO2009085467A8 WO 2009085467 A8 WO2009085467 A8 WO 2009085467A8 US 2008084315 W US2008084315 W US 2008084315W WO 2009085467 A8 WO2009085467 A8 WO 2009085467A8
Authority
WO
WIPO (PCT)
Prior art keywords
control system
compressor
gas turbine
turbine engine
blade tip
Prior art date
Application number
PCT/US2008/084315
Other languages
French (fr)
Other versions
WO2009085467A1 (en
Inventor
Aspi Rustom Wadia
David Scott Clark
Ching-Pang Lee
Andrew Breeze-Stringfellow
Gregory Scott Mcnulty
Original Assignee
General Electric Company
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 Company filed Critical General Electric Company
Priority to DE112008003506T priority Critical patent/DE112008003506T5/en
Priority to GB1011325A priority patent/GB2467893A/en
Priority to CA2710376A priority patent/CA2710376A1/en
Priority to JP2010540701A priority patent/JP2011508148A/en
Publication of WO2009085467A1 publication Critical patent/WO2009085467A1/en
Publication of WO2009085467A8 publication Critical patent/WO2009085467A8/en

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

Abstract

A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.
PCT/US2008/084315 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 WO2009085467A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE112008003506T DE112008003506T5 (en) 2007-12-28 2008-11-21 A compressor blade tip gap control system comprising a plasma actuator, compressor and gas turbine engine having such a control system
GB1011325A GB2467893A (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
CA2710376A CA2710376A1 (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
JP2010540701A JP2011508148A (en) 2007-12-28 2008-11-21 Compressor tip clearance control system including plasma actuator, compressor, and gas turbine engine including the control system

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
US11/966,309 2007-12-28

Publications (2)

Publication Number Publication Date
WO2009085467A1 WO2009085467A1 (en) 2009-07-09
WO2009085467A8 true WO2009085467A8 (en) 2010-07-22

Family

ID=40340572

Family Applications (1)

Application Number Title Priority Date Filing Date
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

Country Status (6)

Country Link
US (1) US20100284795A1 (en)
JP (1) JP2011508148A (en)
CA (1) CA2710376A1 (en)
DE (1) DE112008003506T5 (en)
GB (1) GB2467893A (en)
WO (1) WO2009085467A1 (en)

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* Cited by examiner, † Cited by third party
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US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US20100205928A1 (en) * 2007-12-28 2010-08-19 Moeckel Curtis W Rotor stall sensor system
US8282337B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US8317457B2 (en) * 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
US8348592B2 (en) * 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US8282336B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US20100284785A1 (en) * 2007-12-28 2010-11-11 Aspi Rustom Wadia Fan Stall Detection System
US20100290906A1 (en) * 2007-12-28 2010-11-18 Moeckel Curtis W Plasma sensor stall control system and turbomachinery diagnostics
US20100047060A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Compressor
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
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation
US20100172747A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced compressor duct
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

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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
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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
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WO2009018532A1 (en) * 2007-08-02 2009-02-05 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
US20100047060A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Compressor
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
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
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor

Also Published As

Publication number Publication date
CA2710376A1 (en) 2009-07-09
WO2009085467A1 (en) 2009-07-09
GB201011325D0 (en) 2010-08-18
GB2467893A (en) 2010-08-18
JP2011508148A (en) 2011-03-10
US20100284795A1 (en) 2010-11-11
DE112008003506T5 (en) 2010-11-04

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