Abstract: An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades, and sucking in air from the minimized inner flowpath through a radially inner orifice of a vane faced by the labyrinths. The method further includes directing the sucked in air through the vane, bleeding the air from the vane through a radially outer opening of the vane and through an orifice of an outer casing. The air is collected from the vane into a manifold outside the compression stage. A compressor arrangement for circulating air includes a suction device for sucking in air present in the inner flowpath between labyrinths and the vane, and for sending the air into the vane of the stator. The arrangement also includes a device for bleeding air in the vane of the stator and for sending the air outside the compressor.

Abstract: A turbojet includes a differential gear with a first planetary pinion driven by the shaft of the high pressure spool and a second planetary pinion driven by the shaft of the low pressure spool. The planetary pinions drive satellite pinions mounted in a cage by which the ancillary machines are driven. The satellite pinions and said cage are co-rotary and the mechanical transmission ratio R1 between the high pressure shaft and the first planetary pinion of the differential gear and the transmission ratio R2 between the low pressure shaft and the second planetary pinion of the differential gear are such that the power extraction distribution between the high pressure spool and the low pressure spool at idle speed is between 80%/20% and 20%/80%. The operation of the high pressure compressor is not affected by the maximum power drawn by the ancillary machines.

Abstract: A turbine wheel for a turbomachine, the disk of which comprises upstream and downstream ribs extending in the annular direction around an axis, each blade segment installed on the disk being retained by the disk in an external radial direction using upstream engagement part forming part of the segment root and cooperating with complementary upstream engagement part forming an external radial end of the upstream rib, and downstream engagement part forming part of the root and capable of cooperating with complementary downstream engagement part forming an external radial end of the downstream rib. Furthermore, the upstream and downstream ribs are movable from a separated engagement position to a close position, and vice versa, so that each blade segment can be assembled on the turbine disk.

Abstract: For a compression stage of a compressor comprising several compression stages (28) with a rotor (14) and a stator (26), an outer casing (8) and an inner casing (4) delimiting a flowpath (10) with an <<outer flowpath>> (34) and an <<inner flowpath>> (36), the method comprises an air suction operation in which air sucked in from the inner flowpath is sent into a vane of said stator, and a bleed operation in which air is bled in said vane and is sent outside the compressor. The compressor arrangement for use of the method comprises suction means (42, 44) and bleed means (48, 50).

Abstract: The present invention relates to a twin-spool turbojet with a shaft of the high pressure rotor and a shaft of the low pressure rotor, including ancillary machines such as electric generators, which it drives via mechanical transmission means.

Abstract: The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.

Abstract: The invention relates to a turbine wheel (1) for a turbomachine, the disk (4) of which comprises upstream and downstream ribs (14a, 14b) extending in the annular direction around an axis (2), each blade segment (6) installed on the disk possibly being retained by the disk in an external radial direction using upstream engagement means (16a) forming part of the segment root (8) and capable of cooperating with complementary upstream engagement means (18a) forming an external radial end of the upstream rib, and downstream engagement means (16b) forming part of the root and capable of cooperating with complementary downstream engagement means (18b) forming an external radial end of the downstream rib. Furthermore, the upstream and downstream ribs are designed so that they can be moved from a separated engagement position to a close position, and vice versa, so that each blade segment can be assembled on the turbine disk.

Abstract: The invention relates to a turbomachine (1) for an aircraft comprising a gas generator (4) designed such that hot gases are ejected from a combustion chamber (28) towards the upstream side of the turbomachine, and also comprising a plurality of hollow mixer struts (40) connected to an output (36) from the gas generator through which hot gases can pass, each mixer strut comprising an output mixer portion (40c) located inside the annular fan duct (8) so as to mix the secondary air and the hot gases ejected by these output mixer portions towards the downstream side of the turbomachine.

Abstract: A high bypass ratio turbojet engine comprising a fan rotated by the shaft of a low pressure turbine via a speed reducer is provided with a thrust reverser device by providing the speed reducer with first and second epicyclic gear trains which are mounted in parallel between the low pressure turbine and the fan and which are arranged in such a way as to drive the fan in a first direction of rotation when the engine is operated in a direct thrust mode, and to drive the fan in the opposite direction of rotation when the engine is to be operated in the reverse thrust mode.