SG11201402854VA - Gas turbine engine with axial movable fan variable area nozzle - Google Patents

Gas turbine engine with axial movable fan variable area nozzle

Info

Publication number
SG11201402854VA
SG11201402854VA SG11201402854VA SG11201402854VA SG11201402854VA SG 11201402854V A SG11201402854V A SG 11201402854VA SG 11201402854V A SG11201402854V A SG 11201402854VA SG 11201402854V A SG11201402854V A SG 11201402854VA SG 11201402854V A SG11201402854V A SG 11201402854VA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
variable area
area nozzle
movable fan
Prior art date
Application number
SG11201402854VA
Inventor
Gregory A Kohlenberg
Sean P Zamora
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
Priority claimed from US13/314,365 external-priority patent/US9701415B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201402854VA publication Critical patent/SG11201402854VA/en

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
    • F02K3/075—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
    • 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
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • 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

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)
SG11201402854VA 2011-12-08 2012-12-07 Gas turbine engine with axial movable fan variable area nozzle SG11201402854VA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/314,365 US9701415B2 (en) 2007-08-23 2011-12-08 Gas turbine engine with axial movable fan variable area nozzle
PCT/US2012/068336 WO2013126123A1 (en) 2011-12-08 2012-12-07 Gas turbine engine with axial movable fan variable area nozzle

Publications (1)

Publication Number Publication Date
SG11201402854VA true SG11201402854VA (en) 2014-07-30

Family

ID=49006098

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201402854VA SG11201402854VA (en) 2011-12-08 2012-12-07 Gas turbine engine with axial movable fan variable area nozzle

Country Status (4)

Country Link
EP (1) EP2788609A4 (en)
CN (1) CN104040158A (en)
SG (1) SG11201402854VA (en)
WO (1) WO2013126123A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108005812B (en) * 2017-12-04 2019-06-18 中国航空发动机研究院 Using the intelligent engine of adaptive casing and adaptive fan
US11306681B2 (en) * 2019-01-15 2022-04-19 The Boeing Company Sheared exhaust nozzle
CN112455699B (en) * 2020-11-13 2024-01-02 中国航空工业集团公司沈阳飞机设计研究所 High-fusion aircraft rear body

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5655360A (en) * 1995-05-31 1997-08-12 General Electric Company Thrust reverser with variable nozzle
US6732502B2 (en) * 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
US7845902B2 (en) * 2005-02-15 2010-12-07 Massachusetts Institute Of Technology Jet engine inlet-fan system and design method
WO2008045058A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Operational line management of low pressure compressor in a turbofan engine
WO2008045049A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
FR2910937B1 (en) * 2007-01-02 2009-04-03 Airbus France Sas AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE
US7950237B2 (en) * 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle
US8074440B2 (en) * 2007-08-23 2011-12-13 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US8973364B2 (en) * 2008-06-26 2015-03-10 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
US8739515B2 (en) * 2009-11-24 2014-06-03 United Technologies Corporation Variable area fan nozzle cowl airfoil

Also Published As

Publication number Publication date
CN104040158A (en) 2014-09-10
EP2788609A1 (en) 2014-10-15
WO2013126123A1 (en) 2013-08-29
EP2788609A4 (en) 2015-08-26

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