EP2788609A4 - 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
EP2788609A4
EP2788609A4 EP12869088.0A EP12869088A EP2788609A4 EP 2788609 A4 EP2788609 A4 EP 2788609A4 EP 12869088 A EP12869088 A EP 12869088A EP 2788609 A4 EP2788609 A4 EP 2788609A4
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
variable area
area nozzle
movable fan
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Withdrawn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
EP12869088.0A
Other languages
German (de)
French (fr)
Other versions
EP2788609A1 (en
Inventor
Gregory A Kohlenberg
Sean P Zamora
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.)
Raytheon Technologies 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 US13/314,365 external-priority patent/US9701415B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2788609A1 publication Critical patent/EP2788609A1/en
Publication of EP2788609A4 publication Critical patent/EP2788609A4/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Withdrawn legal-status Critical Current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
    • 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
EP12869088.0A 2011-12-08 2012-12-07 Gas turbine engine with axial movable fan variable area nozzle Withdrawn EP2788609A4 (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 (2)

Publication Number Publication Date
EP2788609A1 EP2788609A1 (en) 2014-10-15
EP2788609A4 true EP2788609A4 (en) 2015-08-26

Family

ID=49006098

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12869088.0A Withdrawn EP2788609A4 (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

Citations (7)

* 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
EP2028359A2 (en) * 2007-08-23 2009-02-25 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US20090277155A1 (en) * 2007-01-02 2009-11-12 Airbus France Nacelle for aircraft jet engine and aircraft including such nacelle
EP2138696A1 (en) * 2008-06-26 2009-12-30 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
US20110120080A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle cowl airfoil

Family Cites Families (4)

* 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
US7845902B2 (en) * 2005-02-15 2010-12-07 Massachusetts Institute Of Technology Jet engine inlet-fan system and design method
US7950237B2 (en) * 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle

Patent Citations (7)

* 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
US20090277155A1 (en) * 2007-01-02 2009-11-12 Airbus France Nacelle for aircraft jet engine and aircraft including such nacelle
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
US20110120080A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle cowl airfoil

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2013126123A1 *

Also Published As

Publication number Publication date
WO2013126123A1 (en) 2013-08-29
EP2788609A1 (en) 2014-10-15
SG11201402854VA (en) 2014-07-30
CN104040158A (en) 2014-09-10

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Legal Events

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RA4 Supplementary search report drawn up and despatched (corrected)

Effective date: 20150723

RIC1 Information provided on ipc code assigned before grant

Ipc: F02K 3/075 20060101AFI20150717BHEP

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

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Effective date: 20170816

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