SE8206772D0 - Three-dimensional auxially translatable convergent/divergent nozzle assembly - Google Patents

Three-dimensional auxially translatable convergent/divergent nozzle assembly

Info

Publication number
SE8206772D0
SE8206772D0 SE8206772A SE8206772A SE8206772D0 SE 8206772 D0 SE8206772 D0 SE 8206772D0 SE 8206772 A SE8206772 A SE 8206772A SE 8206772 A SE8206772 A SE 8206772A SE 8206772 D0 SE8206772 D0 SE 8206772D0
Authority
SE
Sweden
Prior art keywords
unison ring
dimensional
nozzle assembly
flaps
auxially
Prior art date
Application number
SE8206772A
Other languages
English (en)
Other versions
SE449017B (sv
SE8206772L (sv
Inventor
W H Wiley
W M Madden
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 SE8206772D0 publication Critical patent/SE8206772D0/sv
Publication of SE8206772L publication Critical patent/SE8206772L/sv
Publication of SE449017B publication Critical patent/SE449017B/sv

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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated

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)
SE8206772A 1981-12-28 1982-11-26 Munstycksaggregat med varierbar area for gasturbinmotorer SE449017B (sv)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/334,493 US4447009A (en) 1981-12-28 1981-12-28 Three-dimensional axially translatable convergent/divergent nozzle assembly

Publications (3)

Publication Number Publication Date
SE8206772D0 true SE8206772D0 (sv) 1982-11-26
SE8206772L SE8206772L (sv) 1983-06-29
SE449017B SE449017B (sv) 1987-03-30

Family

ID=23307467

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8206772A SE449017B (sv) 1981-12-28 1982-11-26 Munstycksaggregat med varierbar area for gasturbinmotorer

Country Status (5)

Country Link
US (1) US4447009A (sv)
JP (1) JPS58117338A (sv)
DE (1) DE3242823A1 (sv)
IL (1) IL67301A (sv)
SE (1) SE449017B (sv)

Families Citing this family (13)

* 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
US5176323A (en) * 1991-04-15 1993-01-05 General Electric Company Reduced weight nozzle actuation mechanism
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
US5813611A (en) * 1996-09-27 1998-09-29 United Technologies Corporation Compact pressure balanced fulcrum-link 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
US8020386B2 (en) * 2007-08-21 2011-09-20 United Technologies Corporation Rollertrack pivoting axi-nozzle
US8931281B2 (en) 2010-06-07 2015-01-13 United Technologies Corporation External flap retaining mechanism
EP2982854B1 (en) 2014-08-08 2023-03-01 Raytheon Technologies Corporation Convergent divergent exit nozzle for a gas turbine engine
US9835037B2 (en) * 2015-06-22 2017-12-05 General Electric Company Ducted thrust producing system with asynchronous fan blade pitching

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3214904A (en) * 1960-11-28 1965-11-02 Gen Electric Variable area convergent-divergent nozzle and actuation system therefor
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
US4447009A (en) 1984-05-08
IL67301A (en) 1990-07-26
IL67301A0 (en) 1983-03-31
SE449017B (sv) 1987-03-30
JPH0257223B2 (sv) 1990-12-04
SE8206772L (sv) 1983-06-29
DE3242823C2 (sv) 1992-10-29
DE3242823A1 (de) 1983-07-07
JPS58117338A (ja) 1983-07-12

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