VARIABLE CYCLE PROPULSION ENGINE FOR SUPERSONIC AIRCRAFT.

摘要

P A propulsion engine for a supersonic aircraft comprising a primary assembly comprising at least one compressor (2), a combustion chamber (3), a turbine (4) and an ejection assembly (18) and a secondary assembly comprising a compression or blower assembly disposed in an annular channel (7) and an ejection assembly (19) comprises at least one movable blading (6) of the blower rotor secured to the shaft (5) of the primary assembly and placed between an upstream fixed vane (8) for the inlet director and a downstream fixed vane (9) for the rectifier, each of said fixed vanes (8, 9) being associated with a device (10, 11) for adjusting the setting of the blades. / P