FR3081837B1 - Ensemble turbomachine d'aeronef comportant un capot articule - Google Patents

Ensemble turbomachine d'aeronef comportant un capot articule Download PDF

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Publication number
FR3081837B1
FR3081837B1 FR1854855A FR1854855A FR3081837B1 FR 3081837 B1 FR3081837 B1 FR 3081837B1 FR 1854855 A FR1854855 A FR 1854855A FR 1854855 A FR1854855 A FR 1854855A FR 3081837 B1 FR3081837 B1 FR 3081837B1
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FR
France
Prior art keywords
articulated
nacelle
edge
locking
turbomachine assembly
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.)
Active
Application number
FR1854855A
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English (en)
Other versions
FR3081837A1 (fr
Inventor
Jean Geliot
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations 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 Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR1854855A priority Critical patent/FR3081837B1/fr
Priority to US16/418,555 priority patent/US11242159B2/en
Publication of FR3081837A1 publication Critical patent/FR3081837A1/fr
Application granted granted Critical
Publication of FR3081837B1 publication Critical patent/FR3081837B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un ensemble turbomachine (108) d'un aéronef comportant une nacelle (110) comportant une structure, des capots (110a-b) fixés à ladite structure afin de réaliser une surface aérodynamique, un capot articulé (200) comportant quatre bords (202, 204, 206a-b), et disposé en partie haute de la nacelle (110), une articulation disposée au niveau d'un premier bord du capot articulé (200), fixée entre le capot articulé (200) et la structure de la nacelle (110) et qui assure le déplacement du capot articulé (200) entre une position fermée et une position ouverte, un système de verrouillage disposé au niveau d'un deuxième bord du capot articulé (200) opposé au premier bord, où le système de verrouillage comporte : une poignée (208) actionnable depuis l'extérieur de la nacelle (110) entre une première position et une deuxième position, un dispositif de verrouillage qui est mobile entre une position de verrouillage et une position de déverrouillage, et un système de transmission qui déplace le dispositif de verrouillage de la position de verrouillage à la position de déverrouillage lorsque la poignée (208) passe de la première position à la deuxième position et inversement. Une telle nacelle facilite donc le travail des techniciens, puisque le capot articulé peut être ouvert et fermé facilement et rapidement.
FR1854855A 2018-06-05 2018-06-05 Ensemble turbomachine d'aeronef comportant un capot articule Active FR3081837B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1854855A FR3081837B1 (fr) 2018-06-05 2018-06-05 Ensemble turbomachine d'aeronef comportant un capot articule
US16/418,555 US11242159B2 (en) 2018-06-05 2019-05-21 Aircraft turbomachine assembly comprising an articulated cowl

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1854855A FR3081837B1 (fr) 2018-06-05 2018-06-05 Ensemble turbomachine d'aeronef comportant un capot articule
FR1854855 2018-06-05

Publications (2)

Publication Number Publication Date
FR3081837A1 FR3081837A1 (fr) 2019-12-06
FR3081837B1 true FR3081837B1 (fr) 2020-11-27

Family

ID=63036174

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1854855A Active FR3081837B1 (fr) 2018-06-05 2018-06-05 Ensemble turbomachine d'aeronef comportant un capot articule

Country Status (2)

Country Link
US (1) US11242159B2 (fr)
FR (1) FR3081837B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4001120B1 (fr) 2020-11-24 2024-03-20 Airbus Operations (S.A.S.) Assemblage pour un aéronef comportant un mât et une nacelle comportant une casquette équipée de systèmes de mise en tension et de systèmes de centrage
FR3118757B1 (fr) * 2021-01-13 2023-10-06 Airbus Operations Sas Structure secondaire avant d’un mat d’accrochage d’un aeronef
FR3120854B1 (fr) 2021-03-17 2023-06-09 Airbus Operations Sas Mât réacteur d’aéronef comportant un capot mobile

Family Cites Families (24)

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US1136498A (en) * 1914-07-09 1915-04-20 Daniel W Tower Bolt-operating mechanism.
US2355542A (en) * 1942-02-24 1944-08-08 Lane Company Inc Hinge
US3051280A (en) * 1958-04-04 1962-08-28 Boeing Co Outward-opening plug type door for aircraft
US4095311A (en) * 1976-10-04 1978-06-20 Phil Menard Limitee Hinges
US4720065A (en) * 1985-01-24 1988-01-19 The Boeing Company Translatable outward opening plug-type aircraft door and actuating mechanisms therefor
US5938248A (en) * 1997-10-08 1999-08-17 Southco, Inc. Multi-point latching system
US6220546B1 (en) * 1999-12-29 2001-04-24 The Boeing Company Aircraft engine and associated aircraft engine cowl
FR2812911B1 (fr) * 2000-08-11 2002-09-20 Aircelle Sa Entree d'air pour nacelle de grandes dimensions a transportabilite amelioree
US7469862B2 (en) * 2005-04-22 2008-12-30 Goodrich Corporation Aircraft engine nacelle inlet having access opening for electrical ice protection system
FR2901244B1 (fr) * 2006-05-16 2009-01-09 Airbus France Sas Dispositif d'articulation de portes d'une nacelle d'aeronef et nacelle equipee dudit dispositif d'articulation
FR2903666B1 (fr) * 2006-07-11 2008-10-10 Airbus France Sas Ensemble moteur pour aeronef comprenant un capotage aerodynamique de jonction monte sur deux elements distincts
US8661667B2 (en) * 2009-12-15 2014-03-04 United Technologies Corporation Hinge arm repair
EP2829474B1 (fr) * 2013-07-22 2018-11-21 Airbus Defence and Space SA Système de surveillance pour surveiller une unité de verrouillage de capot en deux parties
US11060331B2 (en) * 2013-07-24 2021-07-13 Mra Systems, Llc Engine door and latch assembly
JP2015086638A (ja) * 2013-11-01 2015-05-07 シロキ工業株式会社 ヒンジ装置
FR3015435B1 (fr) * 2013-12-20 2016-02-05 Aircelle Sa Nacelle de turboreacteur comprenant un verrou de demi-parties arriere securise
FR3024435B1 (fr) * 2014-07-31 2016-08-26 Airbus Operations Sas Capot de soufflante pliable guide, pour ensemble moteur d'aeronef
US10060287B2 (en) * 2015-07-09 2018-08-28 Rohr, Inc Pressure relief door assembly
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Also Published As

Publication number Publication date
FR3081837A1 (fr) 2019-12-06
US11242159B2 (en) 2022-02-08
US20200025088A1 (en) 2020-01-23

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