A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.

A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.

An oil transfer unit has a rotating part extending along an axis, a stationary part provided with an oil mouth, and a floating part having a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration; an annular groove is provided between the floating part and the rotating part to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by a hydrostatic seal defined by a radial gap between the cylindrical surfaces; the unit has at least one oil transfer tube, coupled to the stationary part and the floating part in a fluid-tight manner and with freedom of movement, and a connecting rod to prevent rotation of the floating part; the opposite ends of the connecting rod are coupled to the stationary part and floating part by respective spherical joints.

Pitch actuation system for a turbine engine propeller, comprising an actuator, a movable part of which is configured to be connected to blades of the propeller so as to rotate them relative to the blade pitch axes (B), comprising: a transmission screw that can rotationally and translationally move along a longitudinal axis (A), a nut, through which said transmission screw passes and which cooperates with this screw so as to translationally displace along the axis (A) with a view to modifying the pitch of the propeller blades, and means for decoupling between the rotation of the propeller and said nut, which is rotationally fixed; first blade pitch control means, which comprise at least one electric motor setting a component into rotation through a planet reduction gear with a view to modifying the position of the transmission screw; second blade feathering means configured to act on the transmission screw with a view to modifying the pitch of the blades if the first means are inactive, and in that said first planet reduction gear comprises a ring gear rigidly connected to said first component, a planet shaft rigidly connected to said first rotor and a planet carrier rigidly connected to said first housing.

A turboprop engine system for an aircraft includes an engine, a propeller, and a gear train coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction. The engine system also includes a gearbox that houses at least part of the gear train. The gearbox includes a gearbox flow structure and an inlet flow structure that is removably attached to the gearbox. The inlet flow structure and the gearbox flow structure cooperate to define an inlet flow passage to the engine. The inlet flow passage has an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure. The upstream end is configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

Herein provided are methods and systems for a method for controlling autothrottle of an engine. A digital power request is obtained from an autothrottle controller, the digital power request based on an autothrottle input to the autothrottle controller. A manual input mode for the engine is terminated, the manual input mode based on a second power request obtained from a manual input associated with the engine. An autothrottle mode for the engine is engaged to control the engine based on the digital power request.

A pitch actuation system for a turbine engine propeller, comprising an actuator, a movable part of which is designed to be connected to blades of the propeller so as to rotate said blades relative to blade pitch-setting axes, wherein the actuator is an electromechanical actuator and comprises at least two electric motors for driving a common rotor, and a transmission screw rotated by the common rotor, and in that the system further comprises a nut, through which the transmission screw passes and which is designed to cooperate with the blades so as to move them.

The main purpose of the invention is an air circulation device (1) for a turbomachine (10), comprising an air conveyance circuit (2, 4b, 9, 4a, 3) adapted to bring hot bleed air (A1) from the turbomachine (10) to a part to be heated (38), comprising a first segment fixed in rotation to a rotating part (31, 24) and comprising at least one hot air (A2) conveyance conduit (3, 9), and a hot air passage device (4a, 4b), comprising an annular compartment fixed in rotation to the first segment, characterise in that the annular compartment comprises a heat exchanger in contact with external air, and in that the hot air passage device (4a, 4b) comprises a hot air bypass system to deviate air entering into the device and to make it circulate along the heat exchanger when the temperature of this intake air is above a predetermined threshold.

Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.