Abstract: A multiflow turbojet engine generally includes an upstream fan driven by a gas generator having first and second coaxial compressors, an intake case forming a mounting for the rotors of the upstream fan and the first compressor, an inter-compressor case downstream from the intake case and forming a mounting for the rotors of the second compressor, and attachment means for thrust take-up control rods arranged in the inter-compressor case. The turbojet engine also includes a structural force shroud connecting the intake case to the inter-compressor case, of the and a floating first compressor case.

Abstract: A multi-flow turbojet engine generally includes an upstream ducted fan driven by a gas generator, the gas generator having a first and a second compressor, which are coaxial, an inlet case forming a support for the rotors of the upstream ducted fan and of the first compressor, an inter-compressor case downstream of the inlet casing and forming a support for the rotors of the second compressor, attachment means for thrust take-up rods, which attachment means are arranged on the inter-compressor case. The turbojet engine includes at least one axial stress transmission rod for connecting the inlet case to the inter-compressor case.

Abstract: A turbomachine module includes a rotor supporting variable pitch blades, and an inner annular shaft, a blade pitch control device, a device for feathering at least one blade comprising at least one gas generator placed between a body and a movable member. The control device and the feathering device are situated radially between the shaft and the blades, the movable member is coupled with the at least one blade and capable, under the action of the gas generated and/or released by the generator, of being moved into a reference position wherein it entails a feathered position to the at least one blade.

Abstract: Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (24), means (44) for taking off power from said low-pressure shaft, and a fan (28) that is driven by said low-pressure shaft by means of a reduction gear (32), said reduction gear comprising at least one first element (50) that is connected to said low-pressure shaft for conjoint rotation, at least one second element (56) that is connected to said fan for conjoint rotation, and at least one third element (52) that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (60), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis.

Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.

Abstract: Aircraft turbine engine (10), comprising at least one first compressor, an annular combustion chamber (70) and at least one first turbine (46), which define a first flow duct (22) for a primary flow, characterised in that it comprises, between said combustion chamber (70) and said first turbine (46), a device (55, 55?) for discharging at least part of said primary flow.

Abstract: A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.

Abstract: Bypass turbine engine, in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing and an outer casing (13) so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing (13), a rotary shaft comprising, at the upstream end, a movable fan comprising radial blades of which the free ends face the outer casing (13) of the turbine engine so as to compress an air flow at least in the secondary duct, and a plurality of variable-pitch radial stator vanes (5) mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct, and means for individually adjusting the pitch of the radial vanes (5), which comprise a single control ring and rods (25, 30) for connecting said control ring (24) to each of said radial vanes (5).