FR2180440A1 - - Google Patents

Info

Publication number
FR2180440A1
FR2180440A1 FR7213397A FR7213397A FR2180440A1 FR 2180440 A1 FR2180440 A1 FR 2180440A1 FR 7213397 A FR7213397 A FR 7213397A FR 7213397 A FR7213397 A FR 7213397A FR 2180440 A1 FR2180440 A1 FR 2180440A1
Authority
FR
France
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.)
Granted
Application number
FR7213397A
Other versions
FR2180440B1 (fr
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
Priority to FR7213397A priority Critical patent/FR2180440B1/fr
Priority to DE2318607A priority patent/DE2318607C3/de
Priority to US00351578A priority patent/US3807637A/en
Priority to GB1833573A priority patent/GB1418077A/en
Publication of FR2180440A1 publication Critical patent/FR2180440A1/fr
Application granted granted Critical
Publication of FR2180440B1 publication Critical patent/FR2180440B1/fr
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)
FR7213397A 1972-04-17 1972-04-17 Expired FR2180440B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR7213397A FR2180440B1 (fr) 1972-04-17 1972-04-17
DE2318607A DE2318607C3 (de) 1972-04-17 1973-04-13 Verstellbare konvergent-divergente Schubdüse
US00351578A US3807637A (en) 1972-04-17 1973-04-16 Variable-geometry convergent-divergent nozzles for jet propulsion engines
GB1833573A GB1418077A (en) 1972-04-17 1973-04-17 Variable-geometry convergent-divergent nozzles for jet propulsion engines

Applications Claiming Priority (1)

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

Publications (2)

Publication Number Publication Date
FR2180440A1 true FR2180440A1 (fr) 1973-11-30
FR2180440B1 FR2180440B1 (fr) 1976-06-11

Family

ID=9096965

Family Applications (1)

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

Country Status (4)

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

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2397534A1 (fr) * 1977-07-11 1979-02-09 Gen Electric Tuyere d'ejection a section variable perfectionnee
FR2714422A1 (fr) * 1983-01-13 1995-06-30 Snecma Tuyère convergente-divergente, en particulier pour turboréacteur.
FR2714421A1 (fr) * 1980-01-14 1995-06-30 Snecma Tuyère comportant un convergent-divergent réglable, notamment pour moteur à réaction.
FR2724977A1 (fr) * 1980-12-30 1996-03-29 Snecma Tuyere convergente-divergente en particulier pour turboreacteur
EP0855501A1 (fr) * 1997-01-23 1998-07-29 Industria de Turbo Propulsores S.A. Volet divergent pour une tuyère de turbomachine
WO2022096837A1 (fr) * 2020-11-09 2022-05-12 Safran Aircraft Engines Partie arrière de turboréacteur comprenant une tuyère dont des volets comprennent des leviers déplaçables par des parois d'appui amont et aval

Families Citing this family (15)

* 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
FR2474592A1 (fr) * 1980-01-25 1981-07-31 Snecma Dispositif de tuyere de turboreacteur
FR2723145B1 (fr) * 1981-11-24 1996-12-13 Snecma Tuyere convergente-divergente, en particulier pour turboreacteur
FR2734323A1 (fr) * 1985-04-17 1996-11-22 Snecma Perfectionnement aux tuyeres bidimensionnelles comportant en particulier un deviateur de jet
US5235808A (en) * 1990-02-12 1993-08-17 General Electric Company Exhaust nozzle including idle thrust spoiling
US5140809A (en) * 1990-02-12 1992-08-25 General Electric Company Exhaust nozzle idle thrust spoiling method
ES2105929B1 (es) * 1993-11-23 1998-05-01 Sener Ing & Sist Tobera axisimetrica orientable de geometria variable para propulsores de turbina de gas.
US8020386B2 (en) * 2007-08-21 2011-09-20 United Technologies Corporation Rollertrack pivoting axi-nozzle
US7874160B2 (en) * 2007-08-21 2011-01-25 United Technologies Corporation Nozzle-area ratio float bias
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

Citations (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

Patent Citations (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 (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2397534A1 (fr) * 1977-07-11 1979-02-09 Gen Electric Tuyere d'ejection a section variable perfectionnee
FR2714421A1 (fr) * 1980-01-14 1995-06-30 Snecma Tuyère comportant un convergent-divergent réglable, notamment pour moteur à réaction.
FR2724977A1 (fr) * 1980-12-30 1996-03-29 Snecma Tuyere convergente-divergente en particulier pour turboreacteur
US5566884A (en) * 1980-12-30 1996-10-22 Societe Natinale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle for a turbojet engine
FR2714422A1 (fr) * 1983-01-13 1995-06-30 Snecma Tuyère convergente-divergente, en particulier pour turboréacteur.
EP0855501A1 (fr) * 1997-01-23 1998-07-29 Industria de Turbo Propulsores S.A. Volet divergent pour une tuyère de turbomachine
US6098400A (en) * 1997-01-23 2000-08-08 Industrai De Turbo Propulsores, S.A. Divergent petal for gas turbine engine nozzle
WO2022096837A1 (fr) * 2020-11-09 2022-05-12 Safran Aircraft Engines Partie arrière de turboréacteur comprenant une tuyère dont des volets comprennent des leviers déplaçables par des parois d'appui amont et aval
FR3116084A1 (fr) * 2020-11-09 2022-05-13 Safran Aircraft Engines Partie arriere de turboreacteur comprenant une tuyere dont des volets comprennent des leviers deplacables par des parois d'appui amont et aval
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
US3807637A (en) 1974-04-30
DE2318607C3 (de) 1978-03-16
GB1418077A (en) 1975-12-17
DE2318607B2 (de) 1977-08-04
DE2318607A1 (de) 1973-11-08
FR2180440B1 (fr) 1976-06-11

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Legal Events

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CL Concession to grant licences
ST Notification of lapse