SG11201403545SA - Gas turbine engine with fan variable area nozzle - Google Patents

Gas turbine engine with fan variable area nozzle

Info

Publication number
SG11201403545SA
SG11201403545SA SG11201403545SA SG11201403545SA SG11201403545SA SG 11201403545S A SG11201403545S A SG 11201403545SA SG 11201403545S A SG11201403545S A SG 11201403545SA SG 11201403545S A SG11201403545S A SG 11201403545SA SG 11201403545S A SG11201403545S A SG 11201403545SA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
variable area
area nozzle
fan variable
Prior art date
Application number
SG11201403545SA
Inventor
Gregory A Kohlenberg
Sean P Zamora
Frederick M Schwarz
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 US13/340,798 external-priority patent/US20130149112A1/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201403545SA publication Critical patent/SG11201403545SA/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
    • F02K1/09—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
    • 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
SG11201403545SA 2011-12-30 2012-12-28 Gas turbine engine with fan variable area nozzle SG11201403545SA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/340,798 US20130149112A1 (en) 2011-12-08 2011-12-30 Gas turbine engine with fan variable area nozzle
PCT/US2012/071946 WO2013141934A2 (en) 2011-12-30 2012-12-28 Gas turbine engine with fan variable area nozzle

Publications (1)

Publication Number Publication Date
SG11201403545SA true SG11201403545SA (en) 2014-07-30

Family

ID=49223433

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201403545SA SG11201403545SA (en) 2011-12-30 2012-12-28 Gas turbine engine with fan variable area nozzle

Country Status (4)

Country Link
EP (1) EP2798162A4 (en)
CN (1) CN104011337B (en)
SG (1) SG11201403545SA (en)
WO (1) WO2013141934A2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108626023B (en) * 2017-03-23 2019-12-10 中国航发商用航空发动机有限责任公司 turbofan engine with large bypass ratio and exhaust device with variable bypass exhaust area
CN114320612B (en) * 2021-12-08 2022-08-23 北京航空航天大学 Engine outer duct backflow control method and device, engine and aircraft
CN114992670B (en) * 2022-05-12 2023-06-13 中国航发四川燃气涡轮研究院 Stress application integrated support plate with variable blending function

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
FR2906573B1 (en) * 2006-09-29 2008-11-21 Airbus France Sas AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE
WO2008045049A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
EP2064434B1 (en) * 2006-10-12 2012-06-27 United Technologies Corporation Operational line management of low pressure compressor in a turbofan engine
WO2008045071A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
FR2910937B1 (en) * 2007-01-02 2009-04-03 Airbus France Sas AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE
US8074440B2 (en) * 2007-08-23 2011-12-13 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US9010126B2 (en) * 2008-02-20 2015-04-21 United Technologies Corporation Gas turbine engine with variable area fan nozzle bladder system
US8141366B2 (en) 2008-08-19 2012-03-27 United Technologies Corporation Gas turbine engine with variable area fan 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
GB201117824D0 (en) * 2011-10-17 2011-11-30 Rolls Royce Plc Variable area nozzle for gas turbine engine

Also Published As

Publication number Publication date
CN104011337B (en) 2016-08-24
WO2013141934A3 (en) 2013-11-07
WO2013141934A2 (en) 2013-09-26
EP2798162A2 (en) 2014-11-05
EP2798162A4 (en) 2015-08-26
CN104011337A (en) 2014-08-27

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