EP2798162A4 - Gas turbine engine with fan variable area nozzle - Google Patents

Gas turbine engine with fan variable area nozzle

Info

Publication number
EP2798162A4
EP2798162A4 EP12871636.2A EP12871636A EP2798162A4 EP 2798162 A4 EP2798162 A4 EP 2798162A4 EP 12871636 A EP12871636 A EP 12871636A EP 2798162 A4 EP2798162 A4 EP 2798162A4
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
variable area
area nozzle
fan variable
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.)
Withdrawn
Application number
EP12871636.2A
Other languages
German (de)
French (fr)
Other versions
EP2798162A2 (en
Inventor
Gregory A Kohlenberg
Sean P Zamora
Frederick M Schwarz
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.)
RTX Corp
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 EP2798162A2 publication Critical patent/EP2798162A2/en
Publication of EP2798162A4 publication Critical patent/EP2798162A4/en
Withdrawn legal-status Critical Current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
    • 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

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)
EP12871636.2A 2011-12-30 2012-12-28 Gas turbine engine with fan variable area nozzle Withdrawn EP2798162A4 (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 (2)

Publication Number Publication Date
EP2798162A2 EP2798162A2 (en) 2014-11-05
EP2798162A4 true EP2798162A4 (en) 2015-08-26

Family

ID=49223433

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12871636.2A Withdrawn EP2798162A4 (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

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1522710A2 (en) * 2003-10-07 2005-04-13 General Electric Company Gas turbine engine with variable pressure
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
FR2910937A1 (en) * 2007-01-02 2008-07-04 Airbus France Sas Nacelle for high by-pass ratio jet engine of e.g. commercial aircraft, has double acting cylinder to displace wall rear part to vary passage section, and formation device forming barrier at opening to oppose passage of leaks via opening
EP2028359A2 (en) * 2007-08-23 2009-02-25 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
EP2138696A1 (en) * 2008-06-26 2009-12-30 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
EP2157305A2 (en) * 2008-08-19 2010-02-24 United Technologies Corporation Gas turbine engine with variable area fan nozzle
US20110120080A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle cowl airfoil
EP2584184A2 (en) * 2011-10-17 2013-04-24 Rolls-Royce plc Variable area nozzle for gas turbine engine

Family Cites Families (4)

* 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
FR2906573B1 (en) * 2006-09-29 2008-11-21 Airbus France Sas AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE
EP2074319B1 (en) * 2006-10-12 2012-08-15 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
US9010126B2 (en) * 2008-02-20 2015-04-21 United Technologies Corporation Gas turbine engine with variable area fan nozzle bladder system

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1522710A2 (en) * 2003-10-07 2005-04-13 General Electric Company Gas turbine engine with variable pressure
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
FR2910937A1 (en) * 2007-01-02 2008-07-04 Airbus France Sas Nacelle for high by-pass ratio jet engine of e.g. commercial aircraft, has double acting cylinder to displace wall rear part to vary passage section, and formation device forming barrier at opening to oppose passage of leaks via opening
EP2028359A2 (en) * 2007-08-23 2009-02-25 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
EP2138696A1 (en) * 2008-06-26 2009-12-30 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
EP2157305A2 (en) * 2008-08-19 2010-02-24 United Technologies Corporation Gas turbine engine with variable area fan nozzle
US20110120080A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle cowl airfoil
EP2584184A2 (en) * 2011-10-17 2013-04-24 Rolls-Royce plc Variable area nozzle for gas turbine engine

Also Published As

Publication number Publication date
CN104011337A (en) 2014-08-27
WO2013141934A2 (en) 2013-09-26
SG11201403545SA (en) 2014-07-30
WO2013141934A3 (en) 2013-11-07
EP2798162A2 (en) 2014-11-05
CN104011337B (en) 2016-08-24

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Legal Events

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Effective date: 20150723

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Ipc: F02K 3/075 20060101ALI20150717BHEP

Ipc: F01D 25/24 20060101AFI20150717BHEP

Ipc: F02K 3/072 20060101ALI20150717BHEP

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