GB1100099A - Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft - Google Patents

Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft

Info

Publication number
GB1100099A
GB1100099A GB28966/66A GB2896666A GB1100099A GB 1100099 A GB1100099 A GB 1100099A GB 28966/66 A GB28966/66 A GB 28966/66A GB 2896666 A GB2896666 A GB 2896666A GB 1100099 A GB1100099 A GB 1100099A
Authority
GB
United Kingdom
Prior art keywords
flaps
convergent
divergent
nozzle
jet
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
Application number
GB28966/66A
Other languages
English (en)
Inventor
Hans Peter Mehr
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1100099A publication Critical patent/GB1100099A/en
Expired 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
    • F02K1/1269—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 and the internal downstream series having its flaps hinged at their downstream ends on the downstream ends of the flaps of the external downstream series hinged on a fixed structure at their upstream ends
    • 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
    • F02K1/18—Control or regulation automatic
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Supercharger (AREA)
GB28966/66A 1965-12-08 1966-06-28 Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft Expired GB1100099A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US512343A US3386658A (en) 1965-12-08 1965-12-08 Convergent-divergent jet exhaust nozzle for supersonic aircraft

Publications (1)

Publication Number Publication Date
GB1100099A true GB1100099A (en) 1968-01-24

Family

ID=24038695

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28966/66A Expired GB1100099A (en) 1965-12-08 1966-06-28 Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft

Country Status (4)

Country Link
US (1) US3386658A (enExample)
BE (1) BE685546A (enExample)
DE (1) DE1526817A1 (enExample)
GB (1) GB1100099A (enExample)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2729214C1 (ru) * 2019-09-04 2020-08-07 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Регулируемое сверхзвуковое сопло турбореактивного двигателя

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3527409A (en) * 1968-10-11 1970-09-08 United Aircraft Corp Ejector shroud system
US3599875A (en) * 1969-02-10 1971-08-17 United Aircraft Corp Translating air scoop ejector nozzle
FR2096662B1 (enExample) * 1970-05-11 1974-03-15 Snecma
US3973731A (en) * 1975-12-12 1976-08-10 United Technologies Corporation Flap-type two-dimensional nozzle
FR2714421B1 (fr) * 1980-01-14 1996-03-01 Snecma Tuyère comportant un convergent-divergent réglable, notamment pour moteur à réaction.
DE3666072D1 (de) * 1986-08-18 1989-11-09 Rolls Royce Plc Turbomachine ejector nozzles
US5141154A (en) * 1991-04-22 1992-08-25 United Technologies Corporation Variable throat convergent/divergent nozzle
US5261229A (en) * 1992-08-03 1993-11-16 General Electric Company Noise-suppressed exhaust nozzles for jet engines
US5680755A (en) * 1995-09-25 1997-10-28 General Electric Company Convertible ejector selectively cooled thrust vectoring exhaust nozzle
US6164059A (en) * 1995-11-17 2000-12-26 United Technologies Corporation Multi-expansion ejector nozzle with diverging walls
US20060157997A1 (en) * 2005-01-14 2006-07-20 Eastman Kodak Company Multi-positionable rotary vacuum head for product processing
US8356483B2 (en) * 2008-04-10 2013-01-22 United Technologies Corp Gas turbine engine systems involving variable nozzles with sliding doors
US8443931B2 (en) * 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
US9810085B2 (en) * 2011-08-22 2017-11-07 United Technologies Corporation Flap seal for gas turbine engine movable nozzle flap
US9115669B2 (en) * 2011-10-28 2015-08-25 United Technologies Corporation Gas turbine engine exhaust nozzle cooling valve
US10190506B2 (en) 2014-12-02 2019-01-29 United Technologies Corporation Turbomachine bypass flow diverting assembly and method
US10309318B2 (en) 2014-12-02 2019-06-04 United Technologies Corporation Turbomachine flow diverting device and method
ES2890374T3 (es) * 2017-10-30 2022-01-18 Airbus Operations Sl Cono de cola de aeronave que incorpora una APU con admisión de aire anular
CN113374594B (zh) * 2021-06-21 2022-12-20 中国航发沈阳发动机研究所 一种二元喷管扩张段控制机构
CN115217670B (zh) * 2022-05-24 2024-04-26 中国民用航空飞行学院 一种三涵道超声速喷管构型的设计方法

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3214905A (en) * 1960-11-28 1965-11-02 Gen Electric Variable area convergent-divergent nozzle
US3057150A (en) * 1961-03-27 1962-10-09 United Aircraft Corp Two dimensional floating blow-in-door and flap ejector

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2729214C1 (ru) * 2019-09-04 2020-08-07 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Регулируемое сверхзвуковое сопло турбореактивного двигателя

Also Published As

Publication number Publication date
BE685546A (enExample) 1967-02-01
DE1526817A1 (de) 1970-03-26
US3386658A (en) 1968-06-04

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