Abstract: The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and includes at least one ring of rotor blades around the periphery of a wheel driven by the drive shaft for the front fan, and at least two grids of stator vanes disposed on either side of the ring of rotor blades and inside a grid carrier ring. A stationary outer grid and a stator of variable pitch connect the ring to the fan casing.

Abstract: The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and includes at least one ring of rotor blades around the periphery of a wheel driven by the drive shaft for the front fan, and at least two grids of stator vanes disposed on either side of the ring of rotor blades and inside a grid carrier ring. A stationary outer grid and a stator of variable pitch connect the ring to the fan casing.

Abstract: The invention relates to a turbojet having two counter-rotatable fans (3, 5) at the front of an intermediate casing (2), said fans being secured to a counter-rotatable low-pressure compressor (7). The blades (14) of the rear fan (5) extend into the by-pass air flow (F2) from a wheel (15) that surrounds the outer rotor (20) of the low-pressure compressor (7). The distance (L) between the blades (10) of the front fan (3) and the blades (14) of the rear fan (5) is not less than twice the length (l) of the projection onto the axis of the cord-line of the blades (10) of the front fan (3).