Turbojet having a large bypass ratio

Details Turbojet having a large bypass ratio Turbojet having a large bypass ratio

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 3/075 (2006.01) F01D 25/24 (2006.01) F01D 25/28 (2006.01) F02C 3/13 (2006.01) F02C 7/20 (2006.01) F02C 9/18 (2006.01) F02K 1/68 (2006.01)

Patent

CA 2495624

A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.

Turboréacteur comprenant au moins une soufflante, un compresseur, une chambre de combustion, une turbine et une jupe rigide essentiellement rigide fixée sur son extrémité avant à une enveloppe intermédiaire et, sur son extrémité arrière, à une enveloppe d'échappement, la jupe servant à transmettre les forces entre l'enveloppe intermédiaire et l'enveloppe d'échappement.

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