Abstract: A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.

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 a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. Said compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.

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).

Abstract: The casing of the invention is of the type supporting series of stationary blades having disposed between them series of blades that are movable in rotation about a longitudinal axis. In characteristic manner, said casing comprises a main element and, at least facing one of the series of moving blades, an assembly comprising a plate made of a honeycomb material and a covering disposed on the face of the plate facing away from the blades so that said cells are open towards the blades, said covering being provided with holes that open out into cells of the plate, thereby forming open cells, said covering closing other cells of the plate, thereby forming closed cells, a cavity being formed between said plate and the inside face of said main element. Preferably, the casing forms the casing of an axial compressor operating at low pressure in a turbojet engine.

Abstract: The casing of the invention is of the type supporting series of stationary blades having disposed between them series of blades that are movable in rotation about a longitudinal axis. In characteristic manner, said casing comprises a main element and, at least facing one of the series of moving blades, an assembly comprising a plate made of a honeycomb material and a covering disposed on the face of the plate facing away from the blades so that said cells are open towards the blades, said covering being provided with holes that open out into cells of the plate, thereby forming open cells, said covering closing other cells of the plate, thereby forming closed cells, a cavity being formed between said plate and the inside face of said main element. Preferably, the casing forms the casing of an axial compressor operating at low pressure in a turbojet engine.