GB1418077A - Variable-geometry convergent-divergent nozzles for jet propulsion engines - Google Patents

Variable-geometry convergent-divergent nozzles for jet propulsion engines

Info

Publication number
GB1418077A
GB1418077A GB1833573A GB1833573A GB1418077A GB 1418077 A GB1418077 A GB 1418077A GB 1833573 A GB1833573 A GB 1833573A GB 1833573 A GB1833573 A GB 1833573A GB 1418077 A GB1418077 A GB 1418077A
Authority
GB
United Kingdom
Prior art keywords
convergent
flaps
point
flap
link
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
GB1833573A
Other languages
English (en)
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1418077A publication Critical patent/GB1418077A/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
    • F02K1/1223—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
    • 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
    • F05D2250/90—Variable geometry
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Transmission Devices (AREA)
GB1833573A 1972-04-17 1973-04-17 Variable-geometry convergent-divergent nozzles for jet propulsion engines Expired GB1418077A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7213397A FR2180440B1 (enrdf_load_stackoverflow) 1972-04-17 1972-04-17

Publications (1)

Publication Number Publication Date
GB1418077A true GB1418077A (en) 1975-12-17

Family

ID=9096965

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1833573A Expired GB1418077A (en) 1972-04-17 1973-04-17 Variable-geometry convergent-divergent nozzles for jet propulsion engines

Country Status (4)

Country Link
US (1) US3807637A (enrdf_load_stackoverflow)
DE (1) DE2318607C3 (enrdf_load_stackoverflow)
FR (1) FR2180440B1 (enrdf_load_stackoverflow)
GB (1) GB1418077A (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2317432C1 (ru) * 2006-11-30 2008-02-20 Открытое акционерное общество "Климов" Система синхронизации створок сопла турбореактивного двигателя
GB2456386A (en) * 1985-04-17 2009-07-22 Snecma Nozzle assembly for a turbo-jet engine
US12018628B2 (en) 2020-11-09 2024-06-25 Safran Aircraft Engines Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4052007A (en) * 1975-11-25 1977-10-04 United Technologies Corporation Flap-type two-dimensional nozzle
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
FR2714421B1 (fr) * 1980-01-14 1996-03-01 Snecma Tuyère comportant un convergent-divergent réglable, notamment pour moteur à réaction.
FR2474592A1 (fr) * 1980-01-25 1981-07-31 Snecma Dispositif de tuyere de turboreacteur
FR2724977B1 (fr) * 1980-12-30 1996-12-13 Snecma Tuyere convergente-divergente en particulier pour turboreacteur
FR2723145B1 (fr) * 1981-11-24 1996-12-13 Snecma Tuyere convergente-divergente, en particulier pour turboreacteur
FR2714422A1 (fr) * 1983-01-13 1995-06-30 Snecma Tuyère convergente-divergente, en particulier pour turboréacteur.
US5140809A (en) * 1990-02-12 1992-08-25 General Electric Company Exhaust nozzle idle thrust spoiling method
US5235808A (en) * 1990-02-12 1993-08-17 General Electric Company Exhaust nozzle including idle thrust spoiling
ES2105929B1 (es) * 1993-11-23 1998-05-01 Sener Ing & Sist Tobera axisimetrica orientable de geometria variable para propulsores de turbina de gas.
ES2194171T3 (es) * 1997-01-23 2003-11-16 Turbo Propulsores Ind Petalo divergente para una tobera de motor de turbina de gas.
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
US8443931B2 (en) * 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
GB201314667D0 (en) * 2013-08-16 2013-10-02 Rolls Royce Plc A panel attachment system
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
GB2588652A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588653A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588651A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
CN115234402A (zh) * 2022-04-14 2022-10-25 中国航发沈阳发动机研究所 一种轴对称喷管控制机构

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1329959A (fr) * 1962-07-27 1963-06-14 Rolls Royce Moteurs à réaction à tuyère convergente-divergente
FR1537247A (fr) * 1967-08-18 1968-08-23 United Aircraft Corp Tuyère d'éjection articulée à libre flottement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2456386A (en) * 1985-04-17 2009-07-22 Snecma Nozzle assembly for a turbo-jet engine
GB2456386B (en) * 1985-04-17 2010-01-13 Snecma Jet Nozzle
RU2317432C1 (ru) * 2006-11-30 2008-02-20 Открытое акционерное общество "Климов" Система синхронизации створок сопла турбореактивного двигателя
US12018628B2 (en) 2020-11-09 2024-06-25 Safran Aircraft Engines Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls

Also Published As

Publication number Publication date
DE2318607A1 (de) 1973-11-08
FR2180440A1 (enrdf_load_stackoverflow) 1973-11-30
FR2180440B1 (enrdf_load_stackoverflow) 1976-06-11
DE2318607B2 (de) 1977-08-04
US3807637A (en) 1974-04-30
DE2318607C3 (de) 1978-03-16

Similar Documents

Publication Publication Date Title
GB1418077A (en) Variable-geometry convergent-divergent nozzles for jet propulsion engines
US4176792A (en) Variable area exhaust nozzle
GB1293868A (en) An arrangement for controlling and supporting a variable-geometry duct
US4361281A (en) Exhaust nozzle
US3483702A (en) Fan thrust reverser for a jet propulsion plant
GB1533986A (en) Nozzles for gas turbine engines
GB1456280A (en) Variable area exhaust nozzle assemblies
US3979067A (en) Actuating means for a thrust vectoring gas turbine engine exhaust nozzle
US3570247A (en) Jet nozzle thrust spoiling and thrust reversing mechanism
US2995010A (en) Adjustable propulsion nozzles
GB750307A (en) Improvements relating to variable nozzles for gas-turbine jet propulsion engines
US3454227A (en) Free floating articulate ejector nozzle
GB1435405A (en) Variable-geometry convergent-divergent nozzles
US6289670B1 (en) Turbojet engine thrust reverser and exhaust nozzle
US3080711A (en) Penshape exhaust nozzle for supersonic engine
GB1114064A (en) Improvements in and relating to variable area exhaust nozzle
US2986002A (en) Leaky-type exhaust nozzle for jet propulsion devices
US5364029A (en) Axisymmetric convergent/divergent nozzle with external flaps
GB1151273A (en) Variable-Area Nozzle, especially for Jet Engines of Supersonic Aircraft
GB1278801A (en) Jet nozzle for a gas turbine engine
GB1134495A (en) Improvements in air intakes for supersonic jet propulsion engines
GB1254175A (en) Improvements in or relating to jet propulsion nozzles
GB1177560A (en) Jet Nozzle.
GB1173851A (en) Jet Propulsion Nozzle Vectoring Arrangement
US5520336A (en) Nozzle for a jet engine containing an adjustable convergent-divergent portion

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee