Abstract: A fan module with variable pitch blades for a longitudinal axis propulsion assembly. The module includes a rotor through which a rotor shaft runs along the longitudinal axis X and carries the blades of the fan. A system for changing the pitch of the blades includes a mechanism connected to the blades of the fan and a controller acting on the mechanism. The controller has a fixed body and a movable body translatable along the longitudinal axis X relative to the fixed body, and a load transfer bearing arranged between the mechanism and the controller. The fan module includes a power shaft driving the rotor shaft via an epicyclic train speed reducer, the speed reducer including a sun gear connected to the power shaft and a satellite carrier including a fixed annular ferrule secured to a fixed casing. The fixed body of the controller is mounted on the annular ferrule.

Abstract: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first frustoconical wall (42) and upstream to a second frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19?) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).

Abstract: A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary stream and comprising a hub of diameter D1, wherein—the diameter D3 of the fan rotor is greater than 82 inches (2.08 metres),—the pressure ratio of the fan is between 1.10 and 1.35, the turbomachine comprises a low-pressure compressor separate from the fan, the reduction gearbox being interposed between the fan rotor and a turbine shaft of the low-pressure compressor, and wherein the reduction gearbox casing has an outside diameter D2 greater than the diameter D1 of the hub, the pitch diameter D4 of the reduction gearbox ring being between 0.15 and 0.35 times the fan rotor diameter.

Abstract: Disclosed herein is a fan module with variable pitch blades for a propulsion unit, the fan module comprising a rotor carrying the blades and comprising an inner shaft and an outer casing defining between them a space, a control device for controlling the pitch of the blades, and a feathering device for feathering the blades. The rotation of the rotor is guided by a bearing, and the module further comprises means for recovering and guiding a liquid lubricant of the bearing, with the recovery and guidance means being configured to recover and guide said lubricant from an axial upstream end of the casing, axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.

Abstract: Disclosed herein is a fan module with variable pitch blades for a propulsion unit, the fan module comprising a rotor carrying the blades and comprising an inner shaft and an outer casing defining between them a space, a control device for controlling the pitch of the blades, and a feathering device for feathering the blades. The rotation of the rotor is guided by a bearing, and the module further comprises means for recovering and guiding a liquid lubricant of the bearing, with the recovery and guidance means being configured to recover and guide said lubricant from an axial upstream end of the casing, axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.

Abstract: The invention relates to an assembly including a one-piece bladed disk (1), at least one low-pressure compressor rotor (2) and a low-pressure compressor shaft, characterized in that the bladed disk and the low-pressure compressor rotor (2) are both adapted to be shrunk onto the low-pressure compressor shaft and mechanically attached to it by sets of splines. At least one clamping member (16) blocks axially the different collars with respect to the shaft.

Abstract: Fan module with variable-pitch blades for a propulsion system that includes: a rotor supporting the blades, and including an internal shaft and an external shroud, defining between them a space; a pitch control device (22) of the blades that includes a load transfer bearing; a feathering device of the blades; said feathering device includes at least one lever that is articulated around a fixed axis (A) in relation to the rotor, where said lever features a first end located outside said space and a second end located inside said space, and where a flyweight is fastened to the first end and the second end is coupled to said bearing.

Abstract: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first substantially frustoconical wall (42) and upstream to a second substantially frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19?) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).

Abstract: A device for ventilating turbine components in a gas turbine engine which includes first and second turbine rotors mechanically independent of each other, the first turbine rotor includes an HP turbine disk and the second turbine rotor includes an LP turbine disk and with a first circuit for ventilating the LP turbine is disclosed. The device includes an air compression wheel arranged downstream of the HP turbine disk between the HP turbine disk and LP turbine disk in order to assist the circulation of the air in the first circuit.

Abstract: A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.

Abstract: A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.

Abstract: This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.

Abstract: A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. The device comprises an annular element having a coefficient of expansion that is less than that of the platforms of the nozzle, the annular element being secured to the outer platform and being capable of taking up two positions: one position corresponding to no expansion of the platforms, in which the element provides continuity for the profile of the flow passage; and another position corresponding to the platforms having expanded, in which position the element projects into the flow passage so as to reduce its section.

Abstract: An assembly arrangement between an inner race of a bearing and a journal supported in rotation in this bearing includes a journal annular groove and a race annular groove which interact to form an annular channel when they are placed opposite one another. The assembly further includes a retaining ring placed in the annular channel, which prevents a relative movement in translation between the journal and the inner race. The assembly also includes at least one recess of the journal and at least one tooth of the inner race, which interact to prevent a relative movement in rotation between the journal and the inner race.

Abstract: A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Abstract: A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Abstract: An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12).