GB2467893A - 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 PDFInfo
- Publication number
- GB2467893A GB2467893A GB1011325A GB201011325A GB2467893A GB 2467893 A GB2467893 A GB 2467893A GB 1011325 A GB1011325 A GB 1011325A GB 201011325 A GB201011325 A GB 201011325A GB 2467893 A GB2467893 A GB 2467893A
- 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- Withdrawn
Links
- 239000003989 dielectric material Substances 0.000 abstract 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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.
Description
GB 2467893 A continuation (56) cont CORKE ET AL: "SDBD plasma enhanced aerodynamics: concepts, optimization and applications" PROGRESS IN AEROSPACE SCIENCES, OXFORD, GB, vol. 43, no. 7-8, 1 October 2007 (2007-10-01), pages 193-217, XP0223 57023 WIKIPEDIA CONTRIBUTORS: "Dielectric barrier discharge" INTERNET CITATION, [ONLINE] page 1, XP007907353 Retrieved from the Internet: URL: http://en.wikipedia.org/w/index.php?title=Dielectric_ba rrier_discharge&oldid=2551 96896> [retrieved on 2009-0 1-0 1] WIKIPEDIA CONTRIBUTORS: "Plasma (physics)" INTERNET CITATION, [Online] pages 1-16, XP007907356 Retrieved from the Internet URL: http://en.wikipedia.org/w/index.php?title=Plasma_(phy sics)&oldid=2729329> [retrieved on 2009-02-24]
(58) Field of Search by ISA:
INTCLFOID, FO4D Other: EPO-Internal, COMPENDEX, INSPEC, WPI Data
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 |
---|---|
GB201011325D0 GB201011325D0 (en) | 2010-08-18 |
GB2467893A true GB2467893A (en) | 2010-08-18 |
Family
ID=40340572
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1011325A Withdrawn 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 |
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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9039346B2 (en) | 2011-10-17 | 2015-05-26 | General Electric Company | Rotor support thermal control system |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8282337B2 (en) * | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system using stator plasma actuators |
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 |
US8282336B2 (en) * | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system |
US20100205928A1 (en) * | 2007-12-28 | 2010-08-19 | Moeckel Curtis W | Rotor stall sensor system |
US8317457B2 (en) * | 2007-12-28 | 2012-11-27 | General Electric Company | Method of operating a 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 |
US20100047055A1 (en) * | 2007-12-28 | 2010-02-25 | Aspi Rustom Wadia | Plasma Enhanced Rotor |
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 |
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 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005114013A1 (en) * | 2004-05-20 | 2005-12-01 | Rolls-Royce Plc | Sealing arrangement |
EP1906136A1 (en) * | 2006-09-29 | 2008-04-02 | General Electric Company | System for clearance measurement and method of operating the same |
EP1914391A2 (en) * | 2006-10-13 | 2008-04-23 | General Electric Company | Plasma blade tip clearance control |
WO2008154592A2 (en) * | 2007-06-11 | 2008-12-18 | University Of Florida Research Foundation, Inc. | Electrodynamic control of blade clearance leakage loss in turbomachinery applications |
WO2009018532A1 (en) * | 2007-08-02 | 2009-02-05 | University Of Notre Dame Du Lac | Compressor tip gap flow control using plasma actuators |
Family Cites Families (17)
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 |
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 |
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 |
US7628585B2 (en) * | 2006-12-15 | 2009-12-08 | General Electric Company | Airfoil leading edge end wall vortex reducing plasma |
US7736123B2 (en) * | 2006-12-15 | 2010-06-15 | General Electric Company | Plasma induced virtual turbine airfoil trailing edge extension |
US20090169356A1 (en) * | 2007-12-28 | 2009-07-02 | Aspi Rustom Wadia | Plasma Enhanced Compression System |
US8348592B2 (en) * | 2007-12-28 | 2013-01-08 | General Electric Company | Instability mitigation system using rotor plasma actuators |
US20100047060A1 (en) * | 2007-12-28 | 2010-02-25 | Aspi Rustom Wadia | Plasma Enhanced Compressor |
US20090169363A1 (en) * | 2007-12-28 | 2009-07-02 | Aspi Rustom Wadia | Plasma Enhanced Stator |
US20100047055A1 (en) * | 2007-12-28 | 2010-02-25 | Aspi Rustom Wadia | Plasma Enhanced Rotor |
US8282337B2 (en) * | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system using stator plasma actuators |
US8282336B2 (en) * | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system |
-
2007
- 2007-12-28 US US11/966,309 patent/US20100284795A1/en not_active Abandoned
-
2008
- 2008-11-21 GB GB1011325A patent/GB2467893A/en not_active Withdrawn
- 2008-11-21 CA CA2710376A patent/CA2710376A1/en not_active Abandoned
- 2008-11-21 DE DE112008003506T patent/DE112008003506T5/en not_active Withdrawn
- 2008-11-21 JP JP2010540701A patent/JP2011508148A/en active Pending
- 2008-11-21 WO PCT/US2008/084315 patent/WO2009085467A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005114013A1 (en) * | 2004-05-20 | 2005-12-01 | Rolls-Royce Plc | Sealing arrangement |
EP1906136A1 (en) * | 2006-09-29 | 2008-04-02 | General Electric Company | System for clearance measurement and method of operating the same |
EP1914391A2 (en) * | 2006-10-13 | 2008-04-23 | General Electric Company | Plasma blade tip clearance control |
WO2008154592A2 (en) * | 2007-06-11 | 2008-12-18 | University Of Florida Research Foundation, Inc. | Electrodynamic control of blade clearance leakage loss in turbomachinery applications |
WO2009018532A1 (en) * | 2007-08-02 | 2009-02-05 | University Of Notre Dame Du Lac | Compressor tip gap flow control using plasma actuators |
Non-Patent Citations (8)
Title |
---|
CORKE ET AL: "SDBD plasma enhanced aerodynamics: concepts, optimization and applications" PROGRESS IN AEROSPACE SCIENCES, OXFORD, GB, vol. 43, no. 7-8, 1 October 2007 (2007-10-01), pages 193-217, XP022357023 * |
DOUVILLE T ET AL: "Turbine blade tip leakage flow control by partial squealer tip and plasma actuators" AIAA AEROSPACE SCIENCES MEETING, XX, XX, vol. AIAA 2006-20, 1 January 2006 (2006-01-01), pages 263-280, XP009112405 * |
GÞKSEL B ET AL: "Active Flow Control in Turbomachinery Using Phased Plasma Actuators" INTERNET CITATION, [Online] 1 April 2004 (2004-04-01), XP007907306 Retrieved from the Internet: URL:http://www.electrofluidsystems.com/news/Goeksel-ISABE2005.pdf> * |
MORRIS SC ET AL: "Tip clearance control using plasma actuators" AIAA PAPER 2005-782,, 1 January 2005 (2005-01-01), pages 1-8, XP009112406 * |
VAN NESS DK ET AL: "Turbine tip clearance flow control using plasma actuators" AIAA PAPER 2006-21, 1 January 2006 (2006-01-01), pages 1-11, XP009112404 * |
VAN NESS II D K ET AL: "Stereo PIV of a turbine tip clearance flow with plasma actuation" COLLECTION OF TECHNICAL PAPERS; (45TH AIAA AEROSPACE SCIENCES MEETING 2007 - 20070108 TO 20070111 - RENO, NV),, vol. 11, 8 January 2007(2007-01-08), pages 7805-7825, XP009112407 * |
WIKIPEDIA CONTRIBUTORS: "Dielectric barrier discharge" INTERNET CITATION, [ONLINE] page 1, XP007907353 Retrieved from the Internet: URL: http://en.wikipedia.org/w/index.php?title=Dielectric_barrier_discharge&oldid=255196896> [retrieved on 2009-01-01] * |
WIKIPEDIA CONTRIBUTORS: "Plasma (physics)" INTERNET CITATION, [Online] pages 1-16, XP007907356 Retrieved from the Internet URL: http://en.wikipedia.org/w/index.php?title=Plasma_(physics)&oldid=2729329> [retrieved on 2009-02-24] * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9039346B2 (en) | 2011-10-17 | 2015-05-26 | General Electric Company | Rotor support thermal control system |
Also Published As
Publication number | Publication date |
---|---|
DE112008003506T5 (en) | 2010-11-04 |
WO2009085467A8 (en) | 2010-07-22 |
CA2710376A1 (en) | 2009-07-09 |
JP2011508148A (en) | 2011-03-10 |
WO2009085467A1 (en) | 2009-07-09 |
GB201011325D0 (en) | 2010-08-18 |
US20100284795A1 (en) | 2010-11-11 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB2467893A (en) | Compressor blade tip clearance control system with a plasma actuator, compressor and gas turbine engine with such a control system | |
GB2467892A (en) | Compressor and gas turbine engine with a plasma actuator | |
EP1914391A3 (en) | Gas turbine engine blade tip clearance control system with a plasma actuator and corresponding operating method | |
GB2467895A (en) | Plasma enhanced compressor | |
Benini | Progress in gas turbine performance | |
EP2587028A3 (en) | Active clearance control system and method for a gas turbine engine | |
EP2022949B8 (en) | Fan section of a gas turbine engine, corresponding gas turbine engine and operating method | |
EP2487335A3 (en) | Case with ballistic liner | |
MX2012006116A (en) | Exhaust temperature based mode control method for gas turbine and gas turbine. | |
EP2230387A3 (en) | Casing treatment for a gas turbine engine reducing blade tip clearance | |
WO2014105701A3 (en) | Non-integral fan blade platform | |
EP2143888A3 (en) | Steam turbine and method of cooling steam turbine | |
EP2372105A3 (en) | Rotor blade tip clearance control | |
EP3779167A3 (en) | Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings | |
SG142227A1 (en) | Turbine component with tip flagged pedestal cooling | |
EP2112330A3 (en) | Fan blade | |
WO2015102702A3 (en) | Tailored thermal control system for gas turbine engine blade outer air seal array | |
WO2014014535A8 (en) | Air accelerator on tie rod within turbine disk bore | |
EP2236757A3 (en) | Split rotor disk assembly for a gas turbine engine | |
WO2011026468A3 (en) | Turbomachine, and method for producing a structured abradable coating | |
WO2011054341A3 (en) | Sealing arrangement for a gas turbine and such a gas turbine | |
SI2173974T1 (en) | Heat shield segment for a stator of a gas turbine | |
EP3495650B8 (en) | Method of varying an annular fan exit area of a gas turbine engine | |
EP2562368A3 (en) | Rotor asymmetry | |
Sporer et al. | New high-temperature seal system for increased efficiency of gas turbines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |