IL67302A - Means for balancing the loads on a variable area nozzle of a gas turbine engine - Google Patents

Means for balancing the loads on a variable area nozzle of a gas turbine engine

Info

Publication number
IL67302A
IL67302A IL67302A IL6730282A IL67302A IL 67302 A IL67302 A IL 67302A IL 67302 A IL67302 A IL 67302A IL 6730282 A IL6730282 A IL 6730282A IL 67302 A IL67302 A IL 67302A
Authority
IL
Israel
Prior art keywords
balancing
loads
gas turbine
turbine engine
variable area
Prior art date
Application number
IL67302A
Other languages
English (en)
Other versions
IL67302A0 (en
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 IL67302A0 publication Critical patent/IL67302A0/xx
Publication of IL67302A publication Critical patent/IL67302A/xx

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
    • F02K1/1292—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream ends on a substantially axially movable structure

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
IL67302A 1981-12-28 1982-11-18 Means for balancing the loads on a variable area nozzle of a gas turbine engine IL67302A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/334,494 US4440347A (en) 1981-12-28 1981-12-28 Simplified means for balancing the loads on a variable area nozzle

Publications (2)

Publication Number Publication Date
IL67302A0 IL67302A0 (en) 1983-03-31
IL67302A true IL67302A (en) 1986-11-30

Family

ID=23307472

Family Applications (1)

Application Number Title Priority Date Filing Date
IL67302A IL67302A (en) 1981-12-28 1982-11-18 Means for balancing the loads on a variable area nozzle of a gas turbine engine

Country Status (6)

Country Link
US (1) US4440347A (ja)
JP (1) JPS58117339A (ja)
DE (1) DE3242824A1 (ja)
EG (1) EG16017A (ja)
IL (1) IL67302A (ja)
SE (1) SE453768B (ja)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4552309A (en) * 1982-04-07 1985-11-12 Rolls-Royce Inc. Variable geometry nozzles for turbomachines
US5082182A (en) * 1990-08-23 1992-01-21 United Technologies Corporation Thrust vectoring exhaust nozzle
US5261605A (en) * 1990-08-23 1993-11-16 United Technologies Corporation Axisymmetric nozzle with gimbled unison ring
US5150839A (en) * 1991-03-14 1992-09-29 General Electric Company Nozzle load management
US5794850A (en) 1996-09-27 1998-08-18 United Technologies Corporation Enclosed pressure balanced sync ring nozzle
US5813611A (en) * 1996-09-27 1998-09-29 United Technologies Corporation Compact pressure balanced fulcrum-link nozzle
US5833140A (en) * 1996-12-12 1998-11-10 United Technologies Corporation Variable geometry exhaust nozzle for a turbine engine
US6398129B1 (en) 1999-12-29 2002-06-04 United Technologies Corporation Throat configuration for axisymmetric nozzle
US6779336B2 (en) * 2002-07-05 2004-08-24 United Technologies Corporation Cooled variable geometry exhaust nozzle
US6871797B2 (en) * 2003-07-07 2005-03-29 United Technologies Corporation Turbine engine nozzle
US7096661B2 (en) * 2004-03-26 2006-08-29 United Technologies Corporation Axial divergent section slot nozzle
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
US8123150B2 (en) 2010-03-30 2012-02-28 General Electric Company Variable area fuel nozzle
US8931281B2 (en) 2010-06-07 2015-01-13 United Technologies Corporation External flap retaining mechanism

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2972226A (en) * 1955-10-06 1961-02-21 United Aircraft Corp Variable area converging-diverging nozzle
US3730436A (en) * 1971-12-20 1973-05-01 United Aircraft Corp Synchronized exhaust nozzle actuating system
US3792815A (en) * 1972-11-24 1974-02-19 United Aircraft Corp Balanced flap converging/diverging nozzle
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle

Also Published As

Publication number Publication date
DE3242824A1 (de) 1983-07-07
SE453768B (sv) 1988-02-29
JPH0347425B2 (ja) 1991-07-19
US4440347A (en) 1984-04-03
SE8206773L (sv) 1983-06-29
IL67302A0 (en) 1983-03-31
SE8206773D0 (sv) 1982-11-26
EG16017A (en) 1986-12-30
JPS58117339A (ja) 1983-07-12

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