IL163619A0 - Multi-spool by-pass turbofan engine - Google Patents

Multi-spool by-pass turbofan engine

Info

Publication number
IL163619A0
IL163619A0 IL16361903A IL16361903A IL163619A0 IL 163619 A0 IL163619 A0 IL 163619A0 IL 16361903 A IL16361903 A IL 16361903A IL 16361903 A IL16361903 A IL 16361903A IL 163619 A0 IL163619 A0 IL 163619A0
Authority
IL
Israel
Prior art keywords
spool
turbofan engine
pass turbofan
pass
engine
Prior art date
Application number
IL16361903A
Other languages
English (en)
Original Assignee
Williams Int Co Llc
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 Williams Int Co Llc filed Critical Williams Int Co Llc
Publication of IL163619A0 publication Critical patent/IL163619A0/xx

Links

Classifications

    • 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
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
IL16361903A 2002-03-05 2003-03-05 Multi-spool by-pass turbofan engine IL163619A0 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/091,684 US6647708B2 (en) 2002-03-05 2002-03-05 Multi-spool by-pass turbofan engine
PCT/US2003/006645 WO2003076787A1 (en) 2002-03-05 2003-03-05 Multi-spool by-pass turbofan engine

Publications (1)

Publication Number Publication Date
IL163619A0 true IL163619A0 (en) 2005-12-18

Family

ID=27787731

Family Applications (2)

Application Number Title Priority Date Filing Date
IL16361903A IL163619A0 (en) 2002-03-05 2003-03-05 Multi-spool by-pass turbofan engine
IL163619A IL163619A (en) 2002-03-05 2004-08-19 Multi-displacement indirect turbo fan engine

Family Applications After (1)

Application Number Title Priority Date Filing Date
IL163619A IL163619A (en) 2002-03-05 2004-08-19 Multi-displacement indirect turbo fan engine

Country Status (9)

Country Link
US (1) US6647708B2 (zh)
EP (1) EP1485601A4 (zh)
JP (1) JP2005519228A (zh)
CN (2) CN1916386A (zh)
AU (1) AU2003225664A1 (zh)
CA (1) CA2477447A1 (zh)
IL (2) IL163619A0 (zh)
RU (1) RU2004129762A (zh)
WO (1) WO2003076787A1 (zh)

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US7086416B2 (en) * 2004-05-27 2006-08-08 Zimmerman & Jansen, Inc. Valve assembly having a compensating gate
US7246482B2 (en) * 2004-07-16 2007-07-24 Honeywell International, Inc. Gas turbine engine bleed air power assist system and method
US7762084B2 (en) * 2004-11-12 2010-07-27 Rolls-Royce Canada, Ltd. System and method for controlling the working line position in a gas turbine engine compressor
FR2881800B1 (fr) * 2005-02-04 2010-08-27 Hispano Suiza Sa Systeme de commande d'une pluralite de vannes de decharge d'une turbomachine
US20060288688A1 (en) * 2005-06-22 2006-12-28 Jean-Pierre Lair Turbofan core thrust spoiler
WO2007116319A2 (en) 2006-01-20 2007-10-18 Rolls-Royce Power Engineering Plc Bleed off valve system
GB0618072D0 (en) * 2006-09-14 2006-10-25 Rolls Royce Plc Aeroengine nozzle
US7788898B2 (en) * 2006-12-06 2010-09-07 General Electric Company Variable coupling of turbofan engine spools via open differential gear set or simple planetary gear set for improved power extraction and engine operability, with torque coupling for added flexibility
US20080148881A1 (en) * 2006-12-21 2008-06-26 Thomas Ory Moniz Power take-off system and gas turbine engine assembly including same
FR2912782B1 (fr) * 2007-02-19 2009-05-22 Snecma Sa Procede de prelevement d'energie auxiliaire sur un turboreacteur d'avion et turboreacteur equipe pour mettre en oeuvre un tel procede
US8015828B2 (en) * 2007-04-03 2011-09-13 General Electric Company Power take-off system and gas turbine engine assembly including same
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
EP2078837A1 (de) * 2008-01-11 2009-07-15 Siemens Aktiengesellschaft Zapfluftentnahmevorrichtung für einen Verdichter eines Gasturbinentriebwerks
DE102008024022A1 (de) * 2008-05-16 2009-11-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk, insbesondere Flugtriebwerk
US8887485B2 (en) * 2008-10-20 2014-11-18 Rolls-Royce North American Technologies, Inc. Three spool gas turbine engine having a clutch and compressor bypass
US8753075B2 (en) * 2010-07-20 2014-06-17 Rolls-Royce Corporation Fan case assembly and method
US9261019B2 (en) * 2010-12-30 2016-02-16 Rolls-Royce North American Technologies, Inc. Variable cycle gas turbine engine
US20120183398A1 (en) * 2011-01-13 2012-07-19 General Electric Company System and method for controlling flow through a rotor
US9188083B2 (en) * 2011-10-28 2015-11-17 United Technologies Corporation Gas turbine engine with auxiliary fan
US9103227B2 (en) * 2012-02-28 2015-08-11 United Technologies Corporation Gas turbine engine with fan-tied inducer section
US9850821B2 (en) * 2012-02-28 2017-12-26 United Technologies Corporation Gas turbine engine with fan-tied inducer section
US9239004B2 (en) 2012-03-27 2016-01-19 United Technologies Corporation Reverse core gear turbofan
US20130259650A1 (en) * 2012-04-02 2013-10-03 Frederick M. Schwarz Geared turbofan with three turbines with first two co-rotating and third rotating in an opposed direction
US9404389B2 (en) * 2013-09-24 2016-08-02 General Electric Company Passive cooling system for control valve actuators within a negative pressure turbine enclosure using ambient cooling air
US20150176530A1 (en) * 2013-12-19 2015-06-25 United Technologies Corporation Ultra high overall pessure ratio gas turbine engine
US20160047304A1 (en) * 2013-12-19 2016-02-18 United Technologies Corporation Ultra high overall pressure ratio gas turbine engine
CN103939219B (zh) * 2014-04-24 2016-01-27 北京航空航天大学 一种变循环发动机可调机构中的模式转换阀
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
GB201414071D0 (en) * 2014-08-08 2014-09-24 Rolls Royce Plc Gas turbine engine
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US9803557B2 (en) * 2015-01-20 2017-10-31 United Technologies Corporation Gas turbine engine and blocker door assembly
US10012147B2 (en) * 2015-08-17 2018-07-03 United Technologies Corporation Apparatus and method for air particle separator in gas turbine engine
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
CN106523186B (zh) * 2016-12-30 2018-08-10 黄祖辉 喷气发动机及飞机
US10393017B2 (en) 2017-03-07 2019-08-27 Rolls-Royce Corporation System and method for reducing specific fuel consumption (SFC) in a turbine powered aircraft
CN107091162B (zh) * 2017-05-08 2019-12-20 中国航发湖南动力机械研究所 动力涡轮可调式发动机
US10637321B1 (en) * 2018-12-07 2020-04-28 GM Global Technology Operations LLC Motor housings and motor assemblies with controlled radial thermal expansion
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

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US2529973A (en) 1946-05-29 1950-11-14 Rateau Soc Arrangement for the starting of two shaft gas turbine propelling means chiefly on board of aircraft
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US5485717A (en) 1994-06-29 1996-01-23 Williams International Corporation Multi-spool by-pass turbofan engine
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Also Published As

Publication number Publication date
JP2005519228A (ja) 2005-06-30
CN1916386A (zh) 2007-02-21
IL163619A (en) 2007-09-20
EP1485601A4 (en) 2010-07-14
AU2003225664A1 (en) 2003-09-22
CA2477447A1 (en) 2003-09-18
WO2003076787A1 (en) 2003-09-18
CN1324231C (zh) 2007-07-04
CN1639451A (zh) 2005-07-13
EP1485601A1 (en) 2004-12-15
US6647708B2 (en) 2003-11-18
US20030167750A1 (en) 2003-09-11
RU2004129762A (ru) 2006-02-20

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