An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.

A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.

A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

A stator assembly including plural stator vanes distributed around an axis of revolution of the stator assembly, a chord of the stator vane, taken at a root of the stator vane, not overlapping, in the direction of the axis of revolution, a chord of an adjacent stator vane, taken at a root of the adjacent stator vane, and a chord of the stator vane, taken at a tip of the stator vane, overlapping, in the direction of the axis of revolution, a chord of the adjacent stator vane, taken at a tip of the adjacent stator vane.

An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.

An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.

An aircraft power unit is disclosed having an engine, which an output shaft linked to a driveshaft of a fan positioned downstream of the engine. The fan is included in a duct formed by a nacelle of the power unit. The nacelle is linked to the driveshaft of the fan by a nacelle pivot formed downstream of the fan.

A turbomachine of an aircraft comprising an outer casing delimiting with an inner hub, a flow path of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller; and a second propeller downstream of the first propeller, the first propeller being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor, the second propeller being further disposed at a distance between 1.5 and 4 cord lengths from the first propeller defined between the respective axes of shimming of each of the first and second propellers.

In a gas turbine engine, a third bearing having a squeeze film damper is disposed between an outer periphery of an intermediate part in an axial direction of a low pressure system shaft and an inner periphery of an intermediate part in an axial direction a high pressure system shaft. Not only is it possible, by connecting the respective intermediate parts in the axial direction of the low and high pressure system shafts to each other via the third bearing to thus enhance bending stiffness of the low and high pressure system shafts and suppress centrifugal whirling, to prevent vibration from occurring, but it is also possible to suppress transmission of vibration between the low and high pressure system shafts by the squeeze film damper of the third bearing, thereby minimizing transmission of vibration to a casing.

In a gas turbine engine, a third bearing having a squeeze film damper is disposed between an outer periphery of an intermediate part in an axial direction of a low pressure system shaft and an inner periphery of an intermediate part in an axial direction a high pressure system shaft. Not only is it possible, by connecting the respective intermediate parts in the axial direction of the low and high pressure system shafts to each other via the third bearing to thus enhance bending stiffness of the low and high pressure system shafts and suppress centrifugal whirling, to prevent vibration from occurring, but it is also possible to suppress transmission of vibration between the low and high pressure system shafts by the squeeze film damper of the third bearing, thereby minimizing transmission of vibration to a casing.