JPH10103154A5 - - Google Patents

Info

Publication number
JPH10103154A5
JPH10103154A5 JP1997276681A JP27668197A JPH10103154A5 JP H10103154 A5 JPH10103154 A5 JP H10103154A5 JP 1997276681 A JP1997276681 A JP 1997276681A JP 27668197 A JP27668197 A JP 27668197A JP H10103154 A5 JPH10103154 A5 JP H10103154A5
Authority
JP
Japan
Prior art keywords
convergent
flaps
divergent
housing
flap
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.)
Granted
Application number
JP1997276681A
Other languages
English (en)
Japanese (ja)
Other versions
JP3968672B2 (ja
JPH10103154A (ja
Filing date
Publication date
Priority claimed from US08/721,888 external-priority patent/US5794850A/en
Application filed filed Critical
Publication of JPH10103154A publication Critical patent/JPH10103154A/ja
Publication of JPH10103154A5 publication Critical patent/JPH10103154A5/ja
Application granted granted Critical
Publication of JP3968672B2 publication Critical patent/JP3968672B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

JP27668197A 1996-09-27 1997-09-25 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル Expired - Fee Related JP3968672B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/721,888 US5794850A (en) 1996-09-27 1996-09-27 Enclosed pressure balanced sync ring nozzle
US08/721,888 1996-09-27

Publications (3)

Publication Number Publication Date
JPH10103154A JPH10103154A (ja) 1998-04-21
JPH10103154A5 true JPH10103154A5 (enExample) 2005-06-16
JP3968672B2 JP3968672B2 (ja) 2007-08-29

Family

ID=24899728

Family Applications (1)

Application Number Title Priority Date Filing Date
JP27668197A Expired - Fee Related JP3968672B2 (ja) 1996-09-27 1997-09-25 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル

Country Status (5)

Country Link
US (1) US5794850A (enExample)
EP (1) EP0833047B1 (enExample)
JP (1) JP3968672B2 (enExample)
KR (1) KR100452668B1 (enExample)
DE (1) DE69723381T2 (enExample)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2194171T3 (es) * 1997-01-23 2003-11-16 Turbo Propulsores Ind Petalo divergente para una tobera de motor de turbina de gas.
US6212877B1 (en) * 1998-09-04 2001-04-10 General Electric Company Vectoring ring support and actuation mechanism for axisymmetric vectoring nozzle with a universal joint
FR2860046B1 (fr) * 2003-09-19 2005-12-02 Snecma Moteurs Volet chaud commande de tuyere axisymetrique de turboreacteur
US7458221B1 (en) * 2003-10-23 2008-12-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths
US20080072604A1 (en) * 2006-09-26 2008-03-27 United Technologies Corporation Pressure balance control for gas turbine engine nozzle
US7854124B2 (en) * 2006-10-27 2010-12-21 United Technologies Corporation Combined control for supplying cooling air and support air in a turbine engine nozzle
US9719370B2 (en) * 2007-03-30 2017-08-01 United Technologies Corporation Linkage system with wear reduction
US7716932B2 (en) * 2008-07-24 2010-05-18 Spirit Aerosystems, Inc. Dilating fan duct nozzle
US20130145768A1 (en) * 2011-12-08 2013-06-13 Honeywell International Inc. Case assembly with fuel or hydraulic driven vafn actuation systems
US9091230B2 (en) * 2012-05-16 2015-07-28 The Boeing Company Linked ring petal actuation for variable area fan nozzle
WO2014160509A1 (en) 2013-03-13 2014-10-02 Rolls-Royce North American Technologies, Inc. Gas turbine engine with three stream, variable area, vectorable nozzle
US9689346B2 (en) 2013-04-12 2017-06-27 United Technologies Corporation Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface
WO2014200402A1 (en) * 2013-06-14 2014-12-18 Saab Ab Variable-geometry convergent-divergent exhaust nozzle for a jet engine and method for varying the nozzle
US9488130B2 (en) 2013-10-17 2016-11-08 Honeywell International Inc. Variable area fan nozzle systems with improved drive couplings
US10502091B2 (en) 2016-12-12 2019-12-10 United Technologies Corporation Sync ring assembly and associated clevis including a rib
CN112761814A (zh) * 2021-01-15 2021-05-07 中国航发沈阳发动机研究所 一种航空发动机喷管收敛片调节机构
FR3119869B1 (fr) * 2021-02-18 2023-02-10 Safran Aircraft Engines Partie arrière de turboréacteur comprenant une tuyère à loi a9/a8 étendue

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3792815A (en) 1972-11-24 1974-02-19 United Aircraft Corp Balanced flap converging/diverging nozzle
GB1444391A (en) * 1973-05-02 1976-07-28 Rolls Royce Exhaust nozzle structures
FR2244917B2 (enExample) 1973-09-21 1978-01-13 Snecma
US4000854A (en) * 1975-10-02 1977-01-04 General Electric Company Thrust vectorable exhaust nozzle
US4049198A (en) * 1976-06-17 1977-09-20 The United States Of America As Represented By The Secretary Of The Air Force Duct pressure actuated nozzle
GB2254377B (en) * 1981-02-28 1993-03-31 Rolls Royce Pressure balanced variable area nozzle
US4440347A (en) 1981-12-28 1984-04-03 United Technologies Corporation Simplified means for balancing the loads on a variable area nozzle
US4440346A (en) 1981-12-28 1984-04-03 United Technologies Corporation Axially translatable variable area convergent/divergent nozzle
US4420932A (en) * 1982-03-02 1983-12-20 The United States Of America As Represented By The Secretary Of The Air Force Pressure control system for convergent-divergent exhaust nozzle
US4456178A (en) 1982-12-27 1984-06-26 United Technologies Corporation Exhaust nozzle assembly with dual unison ring structure
US5011080A (en) 1990-04-18 1991-04-30 United Technologies Corporation Convergent/divergent nozzle construction
US5215256A (en) 1992-07-16 1993-06-01 Barcza W Kevin Flap hinge arrangement for a convergent/divergent nozzle

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