DE2626405C2 - - Google Patents

Info

Publication number
DE2626405C2
DE2626405C2 DE2626405A DE2626405A DE2626405C2 DE 2626405 C2 DE2626405 C2 DE 2626405C2 DE 2626405 A DE2626405 A DE 2626405A DE 2626405 A DE2626405 A DE 2626405A DE 2626405 C2 DE2626405 C2 DE 2626405C2
Authority
DE
Germany
Prior art keywords
compressor
turbine
flap valve
engine
inlet
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.)
Expired - Lifetime
Application number
DE2626405A
Other languages
German (de)
English (en)
Other versions
DE2626405A1 (de
Inventor
John Robert Cincinnati Ohio Us Simmons
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 DE2626405A1 publication Critical patent/DE2626405A1/de
Application granted granted Critical
Publication of DE2626405C2 publication Critical patent/DE2626405C2/de
Granted legal-status Critical Current

Links

Classifications

    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
DE19762626405 1975-06-16 1976-06-12 Gasturbinentriebwerk mit geteiltem geblaese Granted DE2626405A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/587,135 US4010608A (en) 1975-06-16 1975-06-16 Split fan work gas turbine engine

Publications (2)

Publication Number Publication Date
DE2626405A1 DE2626405A1 (de) 1976-12-30
DE2626405C2 true DE2626405C2 (US08066781-20111129-C00013.png) 1990-08-23

Family

ID=24348504

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19762626405 Granted DE2626405A1 (de) 1975-06-16 1976-06-12 Gasturbinentriebwerk mit geteiltem geblaese

Country Status (8)

Country Link
US (1) US4010608A (US08066781-20111129-C00013.png)
JP (1) JPS6039866B2 (US08066781-20111129-C00013.png)
BE (1) BE843002A (US08066781-20111129-C00013.png)
CA (1) CA1052106A (US08066781-20111129-C00013.png)
DE (1) DE2626405A1 (US08066781-20111129-C00013.png)
FR (1) FR2315007A1 (US08066781-20111129-C00013.png)
GB (1) GB1546722A (US08066781-20111129-C00013.png)
IT (1) IT1062407B (US08066781-20111129-C00013.png)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4100404A1 (de) * 1990-05-11 1991-11-14 Gen Electric Verfahren und vorrichtung zum automatischen bypass-betrieb

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US4222233A (en) * 1977-08-02 1980-09-16 General Electric Company Auxiliary lift propulsion system with oversized front fan
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US4961312A (en) * 1985-03-04 1990-10-09 General Electric Company Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
US4813229A (en) * 1985-03-04 1989-03-21 General Electric Company Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas
DE3606286A1 (de) * 1985-03-04 1986-09-04 General Electric Co., Schenectady, N.Y. Verfahren und einrichtung zum steuern des kuehlmittelstroemungsflusses in einer nachbrennerauskleidung
US4958489A (en) * 1985-03-04 1990-09-25 General Electric Company Means for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
GB2246171B (en) * 1986-06-21 1992-04-08 British Aerospace Improvements in or related to gas turbine engines
US4916896A (en) * 1988-11-02 1990-04-17 Paul Marius A Multiple propulsion with quatro vectorial direction system
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US5680754A (en) * 1990-02-12 1997-10-28 General Electric Company Compressor splitter for use with a forward variable area bypass injector
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US5305599A (en) * 1991-04-10 1994-04-26 General Electric Company Pressure-ratio control of gas turbine engine
US5287697A (en) * 1992-01-02 1994-02-22 General Electric Company Variable area bypass injector seal
JPH0735920Y2 (ja) * 1992-04-17 1995-08-16 旭電化工業株式会社 セグメントコーナー部の止水構造
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US5806303A (en) * 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
US5809772A (en) * 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
US5867980A (en) * 1996-12-17 1999-02-09 General Electric Company Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner
GB2354041B (en) * 2000-07-04 2003-11-19 Adrian Alexander Hubbard Variable mode jet engine-compact
US6684626B1 (en) 2002-07-30 2004-02-03 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
US6711887B2 (en) 2002-08-19 2004-03-30 General Electric Co. Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines
US6763653B2 (en) 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
US6763652B2 (en) 2002-09-24 2004-07-20 General Electric Company Variable torque split aircraft gas turbine engine counter rotating low pressure turbines
US6763654B2 (en) 2002-09-30 2004-07-20 General Electric Co. Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans
US6948306B1 (en) * 2002-12-24 2005-09-27 The United States Of America As Represented By The Secretary Of The Navy Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing
US7320285B1 (en) * 2005-03-31 2008-01-22 The United States Of America As Represented By The Secretary Of The Navy Safe and arm device and method of using the same
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
US8672614B1 (en) * 2004-07-09 2014-03-18 Loren Cook Company Exhaust fan systems
US7185484B2 (en) * 2004-08-11 2007-03-06 General Electric Company Methods and apparatus for assembling a gas turbine engine
US8636241B2 (en) 2005-04-20 2014-01-28 Richard H. Lugg Hybrid jet/electric VTOL aircraft
US20070000232A1 (en) * 2005-06-29 2007-01-04 General Electric Company Gas turbine engine and method of operating same
US7752836B2 (en) * 2005-10-19 2010-07-13 General Electric Company Gas turbine assembly and methods of assembling same
US20080175703A1 (en) * 2007-01-09 2008-07-24 Sonic Blue Aerospace Electric turbine bypass fan and compressor for hybrid propulsion
WO2008063153A2 (en) * 2006-10-12 2008-05-29 United Technologies Corporation Managing low pressure turbine maximum speed in a turbofan engine
GB2443194B (en) 2006-10-24 2008-09-10 Rolls-Royce Plc Gas turbine engine
US7765789B2 (en) * 2006-12-15 2010-08-03 General Electric Company Apparatus and method for assembling gas turbine engines
US8161728B2 (en) * 2007-06-28 2012-04-24 United Technologies Corp. Gas turbines with multiple gas flow paths
US8104265B2 (en) * 2007-06-28 2012-01-31 United Technologies Corporation Gas turbines with multiple gas flow paths
US9359960B2 (en) * 2007-06-28 2016-06-07 United Technologies Corporation Gas turbines with multiple gas flow paths
US20100303604A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company System and method to reduce acoustic signature using profiled stage design
US8689538B2 (en) * 2009-09-09 2014-04-08 The Boeing Company Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan
US20110167831A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Adaptive core engine
US8622687B2 (en) * 2009-09-25 2014-01-07 General Electric Company Method of operating adaptive core engines
US9353684B2 (en) * 2009-12-11 2016-05-31 Northrop Grumman Systems Corporation Aircraft engine airflow modulation apparatus and method for engine bay cooling and cycle flow matching
US9624870B2 (en) 2010-03-26 2017-04-18 Rolls-Royce North American Technologies, Inc. Adaptive fan system for a variable cycle turbofan engine
US10041442B2 (en) * 2010-06-11 2018-08-07 United Technologies Corporation Variable area fan nozzle
US8961114B2 (en) 2010-11-22 2015-02-24 General Electric Company Integrated variable geometry flow restrictor and heat exchanger
US9261019B2 (en) * 2010-12-30 2016-02-16 Rolls-Royce North American Technologies, Inc. Variable cycle gas turbine engine
US9057328B2 (en) * 2011-11-01 2015-06-16 United Technologies Corporation Gas turbine engine with intercooling turbine section
US9140214B2 (en) * 2012-02-28 2015-09-22 United Technologies Corporation Method of using an afterburner to reduce high velocity jet engine noise
US9157366B2 (en) * 2012-05-30 2015-10-13 United Technologies Corporation Adaptive fan with cold turbine
US9341075B2 (en) * 2012-06-25 2016-05-17 United Technologies Corporation Pre-turbine engine case variable area mixing plane
EP2904233A4 (en) * 2012-10-01 2016-06-29 United Technologies Corp GUESTURBINE ENGINE WITH LARGE LIGHTWEIGHT FAN
US9523329B2 (en) * 2013-03-15 2016-12-20 United Technologies Corporation Gas turbine engine with stream diverter
US9920710B2 (en) 2013-05-07 2018-03-20 General Electric Company Multi-nozzle flow diverter for jet engine
US10400710B2 (en) * 2013-05-07 2019-09-03 General Electric Company Secondary nozzle for jet engine
US10309318B2 (en) * 2014-12-02 2019-06-04 United Technologies Corporation Turbomachine flow diverting device and method
US10190506B2 (en) * 2014-12-02 2019-01-29 United Technologies Corporation Turbomachine bypass flow diverting assembly and method
US9333603B1 (en) 2015-01-28 2016-05-10 United Technologies Corporation Method of assembling gas turbine engine section
US10378477B2 (en) * 2015-04-30 2019-08-13 Rolls-Royce North American Technologies Inc. Nozzle for jet engines
US11408343B1 (en) * 2021-05-06 2022-08-09 Raytheon Technologies Corporation Turboshaft engine with axial compressor
US11492918B1 (en) 2021-09-03 2022-11-08 General Electric Company Gas turbine engine with third stream
CN114278617B (zh) * 2021-11-30 2023-04-14 清华大学 一种压缩装置及其流道系统
US11834995B2 (en) 2022-03-29 2023-12-05 General Electric Company Air-to-air heat exchanger potential in gas turbine engines
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4100404A1 (de) * 1990-05-11 1991-11-14 Gen Electric Verfahren und vorrichtung zum automatischen bypass-betrieb

Also Published As

Publication number Publication date
JPS6039866B2 (ja) 1985-09-07
JPS521223A (en) 1977-01-07
CA1052106A (en) 1979-04-10
BE843002A (fr) 1976-10-18
FR2315007B1 (US08066781-20111129-C00013.png) 1980-08-29
GB1546722A (en) 1979-05-31
IT1062407B (it) 1984-10-10
US4010608A (en) 1977-03-08
DE2626405A1 (de) 1976-12-30
FR2315007A1 (fr) 1977-01-14

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Legal Events

Date Code Title Description
8110 Request for examination paragraph 44
D2 Grant after examination
8364 No opposition during term of opposition
8320 Willingness to grant licences declared (paragraph 23)
8328 Change in the person/name/address of the agent

Free format text: VOIGT, R., DIPL.-ING., PAT.-ANW., 6232 BAD SODEN