DE69720358T2 - Kompakte durch Druck ausgeglichene Schubdüse - Google Patents

Kompakte durch Druck ausgeglichene Schubdüse

Info

Publication number
DE69720358T2
DE69720358T2 DE69720358T DE69720358T DE69720358T2 DE 69720358 T2 DE69720358 T2 DE 69720358T2 DE 69720358 T DE69720358 T DE 69720358T DE 69720358 T DE69720358 T DE 69720358T DE 69720358 T2 DE69720358 T2 DE 69720358T2
Authority
DE
Germany
Prior art keywords
flaps
nozzle
convergent
divergent
rotary member
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.)
Expired - Fee Related
Application number
DE69720358T
Other languages
German (de)
English (en)
Other versions
DE69720358D1 (de
Inventor
Alfredo Cires
Jennifer Groceman
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
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of DE69720358D1 publication Critical patent/DE69720358D1/de
Application granted granted Critical
Publication of DE69720358T2 publication Critical patent/DE69720358T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
    • 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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/004—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector by using one or more swivable nozzles rotating about their own axis
    • 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
    • F02K1/15—Control or regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/15—Load balancing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
DE69720358T 1996-09-27 1997-09-29 Kompakte durch Druck ausgeglichene Schubdüse Expired - Fee Related DE69720358T2 (de)

Applications Claiming Priority (1)

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

Publications (2)

Publication Number Publication Date
DE69720358D1 DE69720358D1 (de) 2003-05-08
DE69720358T2 true DE69720358T2 (de) 2003-10-30

Family

ID=24899736

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69720358T Expired - Fee Related DE69720358T2 (de) 1996-09-27 1997-09-29 Kompakte durch Druck ausgeglichene Schubdüse

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

Also Published As

Publication number Publication date
KR19980025050A (ko) 1998-07-06
EP0833046A3 (en) 1999-10-20
US5813611A (en) 1998-09-29
EP0833046B1 (en) 2003-04-02
JPH10103153A (ja) 1998-04-21
DE69720358D1 (de) 2003-05-08
EP0833046A2 (en) 1998-04-01
KR100453669B1 (ko) 2004-12-17

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8339 Ceased/non-payment of the annual fee