FR2379433A1 - SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER - Google Patents

SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER

Info

Publication number
FR2379433A1
FR2379433A1 FR7704141A FR7704141A FR2379433A1 FR 2379433 A1 FR2379433 A1 FR 2379433A1 FR 7704141 A FR7704141 A FR 7704141A FR 7704141 A FR7704141 A FR 7704141A FR 2379433 A1 FR2379433 A1 FR 2379433A1
Authority
FR
France
Prior art keywords
safety system
fan casing
attachment
nacelles
air inlet
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.)
Granted
Application number
FR7704141A
Other languages
French (fr)
Other versions
FR2379433B1 (en
Inventor
Paul Joseph Legrand
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 FR7704141A priority Critical patent/FR2379433A1/en
Priority to GB462778A priority patent/GB1559663A/en
Publication of FR2379433A1 publication Critical patent/FR2379433A1/en
Application granted granted Critical
Publication of FR2379433B1 publication Critical patent/FR2379433B1/fr
Granted legal-status Critical Current

Links

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
    • B64D29/06—Attaching of nacelles, fairings or cowlings

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Système de sécurité pour installation << en nacelles >> sur avion d'un turboréacteur à double-flux 1 du type à soufflante amont délimitée par un carter de soufflante 5 du genre dans lequel un carénage d'entrée d'air 7 est fixé à une bride amont du carter de soufflante 5 tandis qu'un capot de tuyère 9 est fixé à une bride aval du carter de soufflante 5, un capot central 8 en deux parties 8a et 8b recouvrant ledit carter de soufflante Ce système de sécurité consiste en ce que des moyens de liaison supplémentaires assurent, lors de la fermeture du capot central 8, une solidarisation de ce dernier avec respectivement le carénage d'entrée d'air 7 et le capot de tuyère 9, solidarisation qui entre en jeu en cas de défaillance de la liaison normale. Nacelles de turboréacteurs pour l'aviation.Safety system for installation "in nacelles" on an airplane of a bypass turbojet 1 of the upstream fan type delimited by a fan casing 5 of the type in which an air inlet fairing 7 is fixed to an upstream flange of the fan casing 5 while a nozzle cover 9 is fixed to a downstream flange of the fan casing 5, a central cover 8 in two parts 8a and 8b covering said fan casing This safety system consists of that additional connecting means ensure, when the central cowl 8 is closed, an attachment of the latter with respectively the air inlet fairing 7 and the nozzle cowl 9, attachment which comes into play in the event of failure of the normal binding. Aviation turbojet nacelles.

FR7704141A 1977-02-08 1977-02-08 SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER Granted FR2379433A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR7704141A FR2379433A1 (en) 1977-02-08 1977-02-08 SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER
GB462778A GB1559663A (en) 1977-02-08 1978-02-06 Safety arrangements for casing parts of an aircraft jet propulsion engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7704141A FR2379433A1 (en) 1977-02-08 1977-02-08 SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER

Publications (2)

Publication Number Publication Date
FR2379433A1 true FR2379433A1 (en) 1978-09-01
FR2379433B1 FR2379433B1 (en) 1980-11-28

Family

ID=9186710

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7704141A Granted FR2379433A1 (en) 1977-02-08 1977-02-08 SAFETY SYSTEM FOR TURBOREACTOR NACELLE COVER

Country Status (2)

Country Link
FR (1) FR2379433A1 (en)
GB (1) GB1559663A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0453360A1 (en) * 1990-04-19 1991-10-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aviation engine with high bypass ratio and of the type with front contra-rotating fan
EP0475877A1 (en) * 1990-08-31 1992-03-18 United Technologies Corporation Aircraft engine cowling roller attachment
WO1993006006A1 (en) * 1991-09-27 1993-04-01 Short Brothers Plc Ducted fan turbine engine nozzle assembly
EP0733545A1 (en) * 1995-03-21 1996-09-25 AEROSPATIALE Société Nationale Industrielle Turbofan with a floatury nacelle
FR2772342A1 (en) * 1997-12-16 1999-06-18 Aerospatiale PROPELLER ASSEMBLY WITH BLOWER HOODS PROVIDED WITH HOLDING AND POSITIONING SAFETY DEVICES, FOR AIRCRAFT
FR3024754A1 (en) * 2014-08-11 2016-02-12 Snecma CONNECTING ASSEMBLY FOR CARTER PARTS OF A TURBOMACHINE
FR3024753A1 (en) * 2014-08-11 2016-02-12 Snecma CONNECTING ASSEMBLY FOR CARTER PARTS OF A TURBOMACHINE
EP3187421A3 (en) * 2015-12-31 2017-09-06 General Electric Company V-blade and v-groove joint molded composite wear sleeve

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2385382B (en) * 2002-02-13 2006-02-15 Rolls Royce Plc A cowl structure for a gas turbine engine
FR2925120B1 (en) * 2007-12-18 2010-02-19 Snecma INTERMEDIATE CARTER EXTENSION FOR AIRCRAFT TURBOJET ENGINE COMPRISING A SECULATED ANNULAR GROOVE OF RECEPTION OF NACELLE HOODS

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0453360A1 (en) * 1990-04-19 1991-10-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aviation engine with high bypass ratio and of the type with front contra-rotating fan
FR2661213A1 (en) * 1990-04-19 1991-10-25 Snecma AVIATION ENGINE WITH VERY HIGH DILUTION RATES AND OF THE SAID TYPE FRONT CONTRAFAN.
US5157915A (en) * 1990-04-19 1992-10-27 Societe Nationale D'etude Et De Construction De Motors D'aviation Pod for a turbofan aero engine of the forward contrafan type having a very high bypass ratio
EP0475877A1 (en) * 1990-08-31 1992-03-18 United Technologies Corporation Aircraft engine cowling roller attachment
WO1993006006A1 (en) * 1991-09-27 1993-04-01 Short Brothers Plc Ducted fan turbine engine nozzle assembly
US5603471A (en) * 1991-09-27 1997-02-18 Short Brothers Plc Ducted fan turbine engine nozzle assembly
EP0733545A1 (en) * 1995-03-21 1996-09-25 AEROSPATIALE Société Nationale Industrielle Turbofan with a floatury nacelle
FR2772342A1 (en) * 1997-12-16 1999-06-18 Aerospatiale PROPELLER ASSEMBLY WITH BLOWER HOODS PROVIDED WITH HOLDING AND POSITIONING SAFETY DEVICES, FOR AIRCRAFT
WO1999030969A1 (en) * 1997-12-16 1999-06-24 Aerospatiale Societe Nationale Industrielle Aircraft propulsion unit with fan cowls equipped with maintaining and positioning safety elements
FR3024754A1 (en) * 2014-08-11 2016-02-12 Snecma CONNECTING ASSEMBLY FOR CARTER PARTS OF A TURBOMACHINE
FR3024753A1 (en) * 2014-08-11 2016-02-12 Snecma CONNECTING ASSEMBLY FOR CARTER PARTS OF A TURBOMACHINE
EP3187421A3 (en) * 2015-12-31 2017-09-06 General Electric Company V-blade and v-groove joint molded composite wear sleeve

Also Published As

Publication number Publication date
GB1559663A (en) 1980-01-23
FR2379433B1 (en) 1980-11-28

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Legal Events

Date Code Title Description
ST Notification of lapse