JPH10103153A5 - - Google Patents

Info

Publication number
JPH10103153A5
JPH10103153A5 JP1997276680A JP27668097A JPH10103153A5 JP H10103153 A5 JPH10103153 A5 JP H10103153A5 JP 1997276680 A JP1997276680 A JP 1997276680A JP 27668097 A JP27668097 A JP 27668097A JP H10103153 A5 JPH10103153 A5 JP H10103153A5
Authority
JP
Japan
Prior art keywords
convergent
flaps
divergent
actuator
housing
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.)
Ceased
Application number
JP1997276680A
Other languages
English (en)
Japanese (ja)
Other versions
JPH10103153A (ja
Filing date
Publication date
Priority claimed from US08/721,890 external-priority patent/US5813611A/en
Application filed filed Critical
Publication of JPH10103153A publication Critical patent/JPH10103153A/ja
Publication of JPH10103153A5 publication Critical patent/JPH10103153A5/ja
Ceased legal-status Critical Current

Links

JP9276680A 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 Ceased JPH10103153A (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/721,890 US5813611A (en) 1996-09-27 1996-09-27 Compact pressure balanced fulcrum-link nozzle
US08/721,890 1996-09-27

Publications (2)

Publication Number Publication Date
JPH10103153A JPH10103153A (ja) 1998-04-21
JPH10103153A5 true JPH10103153A5 (enExample) 2005-06-16

Family

ID=24899736

Family Applications (1)

Application Number Title Priority Date Filing Date
JP9276680A Ceased JPH10103153A (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) US5813611A (enExample)
EP (1) EP0833046B1 (enExample)
JP (1) JPH10103153A (enExample)
KR (1) KR100453669B1 (enExample)
DE (1) DE69720358T2 (enExample)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6622472B2 (en) * 2001-10-17 2003-09-23 Gateway Space Transport, Inc. Apparatus and method for thrust vector control
FR2857414B1 (fr) * 2003-07-08 2007-06-08 Snecma Moteurs Volet souple de tuyere a section variable de turbomachine
US7032835B2 (en) * 2004-01-28 2006-04-25 United Technologies Corporation Convergent/divergent nozzle with modulated cooling
US7624567B2 (en) 2005-09-20 2009-12-01 United Technologies Corporation Convergent divergent nozzle with interlocking divergent flaps
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
US8205454B2 (en) * 2007-02-06 2012-06-26 United Technologies Corporation Convergent divergent nozzle with edge cooled divergent seals
US7757477B2 (en) * 2007-02-20 2010-07-20 United Technologies Corporation Convergent divergent nozzle with slot cooled nozzle liner
US9719370B2 (en) * 2007-03-30 2017-08-01 United Technologies Corporation Linkage system with wear reduction
US7874160B2 (en) * 2007-08-21 2011-01-25 United Technologies Corporation Nozzle-area ratio float bias
US8020386B2 (en) * 2007-08-21 2011-09-20 United Technologies Corporation Rollertrack pivoting axi-nozzle
FR2983917B1 (fr) * 2011-12-07 2013-12-27 Snecma Tuyere convergente-divergente de turbomachine
US9689346B2 (en) 2013-04-12 2017-06-27 United Technologies Corporation Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface
CN104033276B (zh) * 2014-06-09 2016-05-04 中国航空工业集团公司沈阳发动机设计研究所 一种二元喷管的喉道面积控制机构
CN104033275B (zh) * 2014-06-09 2016-02-17 中国航空工业集团公司沈阳发动机设计研究所 一种二元喷管收敛段控制机构
FR3026774B1 (fr) * 2014-10-07 2020-07-17 Safran Aircraft Engines Turbomachine comportant un dispositif de freinage du rotor de soufflante.
US9856956B2 (en) * 2015-01-20 2018-01-02 United Technologies Corporation Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track
US9951717B2 (en) 2015-04-15 2018-04-24 Hamilton Sundstrand Corporation Asymmetric load compensation system
FR3062425B1 (fr) * 2017-01-30 2021-01-08 Safran Aircraft Engines Circuit d'alimentation en carburant de turbomachine
FR3062422B1 (fr) * 2017-01-30 2021-05-21 Safran Aircraft Engines Systeme d'alimentation en carburant d'une turbomachine
CN111828196B (zh) * 2020-07-04 2022-11-01 峰特(浙江)新材料有限公司 一种航空发动机尾喷管
CN112431694B (zh) * 2020-11-20 2021-11-05 哈尔滨工程大学 一种使用柔性材料和外置桁架结构的可展开喷管
CN114109645B (zh) * 2021-11-12 2023-12-19 中国航发沈阳发动机研究所 一种轴对称收扩喷管运动机构
CN113864078B (zh) * 2021-12-03 2022-02-22 中国航发沈阳发动机研究所 一种高隐身二元矢量喷管
US20240140611A1 (en) * 2022-10-31 2024-05-02 The Boeing Company Exhaust systems having adjustable nozzles and related methods

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB858579A (en) * 1957-01-17 1961-01-11 Havilland Engine Co Ltd Adjustable propulsion nozzles
US3792815A (en) * 1972-11-24 1974-02-19 United Aircraft Corp Balanced flap converging/diverging nozzle
FR2227433B1 (enExample) * 1973-04-27 1975-08-22 Snecma
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
US4447009A (en) * 1981-12-28 1984-05-08 United Technologies Corporation Three-dimensional axially translatable convergent/divergent nozzle assembly
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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