SG11201402934YA - Gas turbine engine with compressor inlet guide vane positioned for starting - Google Patents

Gas turbine engine with compressor inlet guide vane positioned for starting

Info

Publication number
SG11201402934YA
SG11201402934YA SG11201402934YA SG11201402934YA SG11201402934YA SG 11201402934Y A SG11201402934Y A SG 11201402934YA SG 11201402934Y A SG11201402934Y A SG 11201402934YA SG 11201402934Y A SG11201402934Y A SG 11201402934YA SG 11201402934Y A SG11201402934Y A SG 11201402934YA
Authority
SG
Singapore
Prior art keywords
starting
gas turbine
turbine engine
guide vane
inlet guide
Prior art date
Application number
SG11201402934YA
Other languages
English (en)
Inventor
Eric J Wehmeier
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201402934YA publication Critical patent/SG11201402934YA/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • 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
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • 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
    • F05D2260/00—Function
    • F05D2260/85—Starting
    • 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
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/092—Purpose of the control system to cope with emergencies in particular blow-out and relight

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
SG11201402934YA 2012-01-31 2013-01-17 Gas turbine engine with compressor inlet guide vane positioned for starting SG11201402934YA (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US201261592667P 2012-01-31 2012-01-31
US13/367,742 US20130192195A1 (en) 2012-01-31 2012-02-07 Gas turbine engine with compressor inlet guide vane positioned for starting
PCT/US2013/021799 WO2013154638A1 (fr) 2012-01-31 2013-01-17 Turbine à gaz dotée d'une aube guide d'entrée de compresseur positionnée pour le démarrage

Publications (1)

Publication Number Publication Date
SG11201402934YA true SG11201402934YA (en) 2014-09-26

Family

ID=48869036

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201402934YA SG11201402934YA (en) 2012-01-31 2013-01-17 Gas turbine engine with compressor inlet guide vane positioned for starting

Country Status (4)

Country Link
US (2) US20130192195A1 (fr)
EP (1) EP2809921B1 (fr)
SG (1) SG11201402934YA (fr)
WO (1) WO2013154638A1 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201505113D0 (en) * 2015-03-26 2015-05-06 Rolls Royce Plc Variable inlet guide vane scheduling
FR3049008B1 (fr) * 2016-03-15 2018-03-02 Safran Aircraft Engines Turboreacteur comprenant un arbre basse pression supercritique
US10724443B2 (en) 2016-05-24 2020-07-28 General Electric Company Turbine engine and method of operating
CN106570213B (zh) * 2016-10-11 2019-07-16 北京航空航天大学 可变进口导流叶片的设计方法及叶片、压气机
GB201803038D0 (en) 2018-02-26 2018-04-11 Rolls Royce Plc Methods and apparatus for controlling at least a part of a start-up or re light process of a gas turbine engine
GB201819695D0 (en) 2018-12-03 2019-01-16 Rolls Royce Plc Methods and apparatus for controlling at least part of a start-up or re-light process of a gas turbine engine
GB201819694D0 (en) 2018-12-03 2019-01-16 Rolls Royce Methods and apparatus for controlling at least part of a start-up or re-light process of a gas turbine engine
GB201819696D0 (en) 2018-12-03 2019-01-16 Rolls Royce Plc Methods and apparatus for controlling at least part of a start-up or re-light process of a gas turbine engine
US11578661B2 (en) 2019-09-19 2023-02-14 Pratt & Whitney Canada Corp. Systems and methods for starting a gas turbine engine
US11668253B2 (en) * 2020-10-16 2023-06-06 Pratt & Whitney Canada Corp. System and method for providing in-flight reverse thrust for an aircraft
US11898500B2 (en) * 2020-12-22 2024-02-13 Textron Innovations Inc. Inlet configuration enabling rapid in-flight engine restart
US11814969B2 (en) * 2021-07-21 2023-11-14 Pratt & Whitney Canada Corp. Gas turbine engine with low-pressure compressor bypass

Family Cites Families (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3287906A (en) 1965-07-20 1966-11-29 Gen Motors Corp Cooled gas turbine vanes
GB1350431A (en) 1971-01-08 1974-04-18 Secr Defence Gearing
US3892358A (en) 1971-03-17 1975-07-01 Gen Electric Nozzle seal
US4069661A (en) * 1975-06-02 1978-01-24 The United States Of America As Represented By The United States National Aeronautics And Space Administration Variable mixer propulsion cycle
US4130872A (en) 1975-10-10 1978-12-19 The United States Of America As Represented By The Secretary Of The Air Force Method and system of controlling a jet engine for avoiding engine surge
GB1516041A (en) 1977-02-14 1978-06-28 Secr Defence Multistage axial flow compressor stators
US4292802A (en) 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
GB2041090A (en) 1979-01-31 1980-09-03 Rolls Royce By-pass gas turbine engines
US4251987A (en) 1979-08-22 1981-02-24 General Electric Company Differential geared engine
US5107674A (en) 1990-03-30 1992-04-28 General Electric Company Control for a gas turbine engine
US5125597A (en) 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5349814A (en) 1993-02-03 1994-09-27 General Electric Company Air-start assembly and method
US5447411A (en) 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system
GB9313905D0 (en) 1993-07-06 1993-08-25 Rolls Royce Plc Shaft power transfer in gas turbine engines
US5524847A (en) 1993-09-07 1996-06-11 United Technologies Corporation Nacelle and mounting arrangement for an aircraft engine
US5433674A (en) 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
US5778659A (en) 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
EP0839285B1 (fr) 1994-12-14 2001-07-18 United Technologies Corporation Limitation du dechrochage tournant et des cretes dans un compresseur, a l'aide de mesures d'asymetrie d'ecoulement d'air
US5845483A (en) 1996-04-10 1998-12-08 General Electric Company Windmill engine starting system with fluid driven motor and pump
US5857836A (en) 1996-09-10 1999-01-12 Aerodyne Research, Inc. Evaporatively cooled rotor for a gas turbine engine
US5975841A (en) 1997-10-03 1999-11-02 Thermal Corp. Heat pipe cooling for turbine stators
US6223616B1 (en) 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US6318070B1 (en) 2000-03-03 2001-11-20 United Technologies Corporation Variable area nozzle for gas turbine engines driven by shape memory alloy actuators
US6814541B2 (en) 2002-10-07 2004-11-09 General Electric Company Jet aircraft fan case containment design
US7021042B2 (en) 2002-12-13 2006-04-04 United Technologies Corporation Geartrain coupling for a turbofan engine
EP1666731A1 (fr) * 2004-12-03 2006-06-07 ALSTOM Technology Ltd Méthode d'opération d'un turbocompresseur
US7448199B2 (en) * 2005-04-29 2008-11-11 General Electric Company Self powdered missile turbojet
WO2007038673A1 (fr) 2005-09-28 2007-04-05 Entrotech Composites, Llc Preimpregnes sans doublure, articles composites a partir de ceux-ci et procedes associes
US7591754B2 (en) 2006-03-22 2009-09-22 United Technologies Corporation Epicyclic gear train integral sun gear coupling design
US20070240426A1 (en) * 2006-04-12 2007-10-18 General Electric Company Mehtod and controller for operating a gas turbine engine
US7926260B2 (en) 2006-07-05 2011-04-19 United Technologies Corporation Flexible shaft for gas turbine engine
US7694505B2 (en) 2006-07-31 2010-04-13 General Electric Company Gas turbine engine assembly and method of assembling same
US7997085B2 (en) * 2006-09-27 2011-08-16 General Electric Company Gas turbine engine assembly and method of assembling same
US9328666B2 (en) * 2006-10-12 2016-05-03 United Technologies Corporation Variable area nozzle assisted gas turbine engine restarting
US8017188B2 (en) 2007-04-17 2011-09-13 General Electric Company Methods of making articles having toughened and untoughened regions
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8074440B2 (en) * 2007-08-23 2011-12-13 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US8205432B2 (en) 2007-10-03 2012-06-26 United Technologies Corporation Epicyclic gear train for turbo fan engine
US8172716B2 (en) 2009-06-25 2012-05-08 United Technologies Corporation Epicyclic gear system with superfinished journal bearing
US20110171007A1 (en) 2009-09-25 2011-07-14 James Edward Johnson Convertible fan system
US20110176913A1 (en) 2010-01-19 2011-07-21 Stephen Paul Wassynger Non-linear asymmetric variable guide vane schedule
US10641179B2 (en) * 2016-11-07 2020-05-05 General Electric Company System and method for starting gas turbine engines
GB201803038D0 (en) * 2018-02-26 2018-04-11 Rolls Royce Plc Methods and apparatus for controlling at least a part of a start-up or re light process of a gas turbine engine
US11745863B2 (en) * 2019-03-05 2023-09-05 Pratt & Whitney Canada Corp. Method and system for engine windmilling control

Also Published As

Publication number Publication date
WO2013154638A1 (fr) 2013-10-17
US20130192195A1 (en) 2013-08-01
EP2809921A4 (fr) 2015-10-21
EP2809921B1 (fr) 2018-06-13
US20140223916A1 (en) 2014-08-14
US11208950B2 (en) 2021-12-28
EP2809921A1 (fr) 2014-12-10

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