A variable cycle engine for supersonic aircraft.

摘要

A propulsion engine for 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 set of compression or fan, placed in an annular channel (7) and an ejection assembly (19) includes at least one movable blading (6) of the fan rotor secured to the shaft (5) of the primary assembly and placed between an upstream stationary blading (8) of the inlet guide and stationary blading the downstream side (9) of the flow-straightener, each of the fixed blades (8, 9) being associated with a device (10, 11) for adjusting the setting of the blades.