Abstract: A module having a longitudinal axis, a hydraulic actuator, and a pump for supplying the hydraulic actuator with fluid, the pump can include axial pistons intended to be movable to rotate about the longitudinal axis and configured to transfer the fluid to the hydraulic actuator, a connecting plate connected to the axial pistons and engaging with an annular main plate centered on the longitudinal axis intended to be rotated about the longitudinal axis and tilted relative to the longitudinal axis, the connecting plate being arranged between the main plate and the axial pistons, the axial pistons being movable to rotate in a direction parallel to the longitudinal axis, the tilting of the main plate resulting in the movement of the axial pistons in the direction.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including: a hydraulic actuator capable of rotating about the longitudinal axis (X) and configured to rotate the vanes about their pitch axes (C), a supply pump for supplying fluid to the hydraulic actuator, the supply pump including a drive shaft capable of rotating about the longitudinal axis (X) and a shell that is rotationally fixed relative to the longitudinal axis (X), and an electric machine configured to operate the supply pump, the electric machine having a rotary member for driving the drive shaft and a fixed member that is rotationally fixed relative to the longitudinal axis (X).

Abstract: Module for mounting a turbomachine fan blade, including: a blade force take-up device, a blade support able to pivot about a radial axis and configured to be engaged axially inside the device, the support and the device being mutually configured to ensure a clamping of the support against the device and an axial retention of the support inside the device; the support and the device each including, on their respective surfaces in cooperation, an alternation of conical seats and recesses making it possible alternatively, on the one hand, when the recesses of one surface are in geometric correspondence with the seats of the other surface, to axially slide the support relative to the device, and on the other hand, when the seats of both surfaces are in geometric correspondence with each other, to prevent any axial sliding movement of the support relative to the device.

Abstract: A fluid transfer device for a turbomachine with longitudinal axis X, which includes a stator portion intended to be connected to a stator equipment of the turbomachine and a rotor portion engaged in the stator portion. The stator equipment including at least one conduit fluidly connected to at least one pipeline of the stator portion, the stator portion and the stator equipment including an attachment interface intended to releasably receive attachment members, the attachment interface and the attachment members being configured so as to make a sealed coincidence of the pipelines and conduit, and the transfer device comprising at least one passage allowing the access of an external tool upstream of the transfer device for accessing the attachment members and passing through the transfer device in either side.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including a hydraulic actuator capable of rotating about the longitudinal axis and configured to rotate the vanes about their pitch axes, a pump for supplying fluid to the hydraulic actuator, including a transmission shaft and a placed around the transmission shaft and rotating as one with the drive shaft, and an electric machine including a rotor rotating as one with the transmission shaft and a stator rotationally fixed relative to the longitudinal axis. The stator can be connected to a power supply cable passing through a passage provided in the third element of the speed reducing gear.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including a hydraulic actuator capable of rotating about the longitudinal axis and configured to rotate the vanes about their pitch axes, a pump for supplying fluid to the hydraulic actuator, including a transmission shaft and a placed around the transmission shaft and rotating as one with the drive shaft, and an electric machine including a rotor rotating as one with the transmission shaft and a stator rotationally fixed relative to the longitudinal axis. The stator can be connected to a power supply cable passing through a passage provided in the third element of the speed reducing gear.

Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Abstract: A reversible hydraulic pump for setting the pitch of a propellor of a turboprop can include two barrels connected by a transmission shaft. The first and second barrels are connected to the transmission shaft via first and second clutch means so that, when the transmission shaft rotates in a first direction, only the first barrel is rotated by the transmission shaft, and so that, when the transmission shaft rotates in a second direction opposite to the first direction, only the second barrel is rotated by the transmission shaft.

Abstract: Module for mounting a turbomachine fan blade, including: a blade force take-up device, a blade support able to pivot about a radial axis and configured to be engaged axially inside the device, the support and the device being mutually configured to ensure a clamping of the support against the device and an axial retention of the support inside the device; the support and the device each including, on their respective surfaces in cooperation, an alternation of conical seats and recesses making it possible alternatively, on the one hand, when the recesses of one surface are in geometric correspondence with the seats of the other surface, to axially slide the support relative to the device, and on the other hand, when the seats of both surfaces are in geometric correspondence with each other, to prevent any axial sliding movement of the support relative to the device.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including: a hydraulic actuator capable of rotating about the longitudinal axis (X) and configured to rotate the vanes about their pitch axes (C), a supply pump for supplying fluid to the hydraulic actuator, the supply pump including a drive shaft capable of rotating about the longitudinal axis (X) and a shell that is rotationally fixed relative to the longitudinal axis (X), and an electric machine configured to operate the supply pump, the electric machine having a rotary member for driving the drive shaft and a fixed member that is rotationally fixed relative to the longitudinal axis (X).

Abstract: A fan module having variable-pitch blades is configured for use with for a propulsion unit having a longitudinal axis. The fan module includes a rotary casing carrying the blades and a pitch-changing system. The pitch-changing system includes a control device that includes an annular actuator having a stationary body added onto the rotary casing and a body configured to translate with respect to the stationary body along the longitudinal axis. A linking mechanism includes a synchronizing ring coupled to the mobile body, connected to the blades and configured to be translated along the longitudinal axis by the mobile body so as to change the pitch of the blades. A feathering device includes fly-weights coupled to the ring by a connecting rod of which the ends include ball-and-socket joints.

Abstract: An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.

Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Abstract: The invention relates to a turbomachine assembly (1) comprising: a compressor (30), an isobaric combustion chamber (40), a piston engine (7) comprising: a shell (70), and a piston (72) movably mounted inside the shell (70) and defining with the shell (70) a variable-volume piston chamber (74), a turbine (50), and a differential transmission mechanism (8).

Abstract: The present invention relates to an assembly for a turbomachine (1) comprising: a compressor (30), an isochoric combustion chamber (7), an isobaric combustion chamber (40), and a turbine (50).

Abstract: The present invention relates to an assembly for a turbomachine (1) comprising: a compressor (30), an isochoric combustion chamber (7), an isobaric combustion chamber (40), and a turbine (50).

Abstract: The invention relates to a turbomachine assembly (1) comprising: a compressor (30), an isobaric combustion chamber (40), a piston engine (7) comprising: a shell (70), and a piston (72) movably mounted inside the shell (70) and defining with the shell (70) a variable-volume piston chamber (74), a turbine (50), and a differential transmission mechanism (8).