Turbojet engine suspension using a double rear support

Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to t...

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Bibliographische Detailangaben
1. Verfasser:	Bellabal, Francois Robert
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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