Abstract: An aircraft cabin blower system comprises a cabin blower including a compressor configured to provide air to a cabin of the aircraft; a variable drive system configured to drive the compressor and including an electric variator and a summing gearbox; and a main transmission configured, when operating in a blower mode, to receive mechanical power from a gas turbine engine and input mechanical power to the summing gearbox in a forward direction; and configured, when operating in a starter mode, to receive mechanical power from the summing gearbox and input mechanical power to the gas turbine engine. The aircraft cabin blower system further includes a first one-way rotation device adapted to permit free rotation of the main transmission in the forward direction and to prevent rotation of the main transmission in a reverse direction opposite to the forward direction.

Abstract: A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

Abstract: An aircraft cabin blower system comprises a cabin blower including a compressor configured to provide air to a cabin of the aircraft; a variable drive system configured to drive the compressor and including an electric variator and a summing gearbox; and a main transmission configured, when operating in a blower mode, to receive mechanical power from a gas turbine engine and input mechanical power to the summing gearbox in a forward direction; and configured, when operating in a starter mode, to receive mechanical power from the summing gearbox and input mechanical power to the gas turbine engine. The aircraft cabin blower system further includes a first one-way rotation device adapted to permit free rotation of the main transmission in the forward direction and to prevent rotation of the main transmission in a reverse direction opposite to the forward direction.

Abstract: A gas turbine engine (10) for an aircraft is disclosed. The gas turbine engine (10) comprises a mechanical power converter (42) arranged to receive an input drive (44) and produce an output drive (46). The output drive (46) has the same rotational direction as the input drive (44). The gas turbine engine further comprises a stationary supporting structure arranged to provide a stationary support for the mechanical power converter (42). The stationary supporting structure comprises one or more structural support aerofoils (24a-24h). A method (100) of supporting a mechanical power converter (42) in a gas turbine engine (10) is also disclosed.

Abstract: A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

Abstract: A vane arrangement for a compressor of a gas turbine engine comprises a plurality of circumferentially arranged vanes, a plurality of levers and a control ring. Each vane comprises a fixed upstream portion secured to a casing and a movable downstream portion pivotally mounted to the casing. The movable portion of each vane is pivotally mounted at the upstream end of the movable portion adjacent the fixed portion of the respective vane. The movable portion of each vane has a spindle extending through an aperture in the casing. Each aperture in the casing has an elongate shape in cross-section and each aperture has a bush arranged within the aperture and around the spindle to fill the elongate shaped aperture. The downstream end of the fixed portion of each vane has substantially the same shape as the upstream end of the movable portion of the respective vane.

Abstract: A variable vane arrangement (36) for a compressor (26) of a gas turbine engine (10) comprises a plurality of circumferentially arranged vanes (38), a plurality of operating levers (64) and a control ring (66). Each vane (38) comprises a fixed upstream portion (40) secured to a casing (30) of the compressor (26) and a movable downstream portion (42) pivotally mounted to the casing (30). The movable portion (42) of each vane (38) is pivotally mounted about an axis (Y) at the upstream end (52) of the movable portion (42) adjacent the fixed portion (40) of the respective vane (38). The movable portion (42) of each vane (38) has a spindle (60) arranged to extend through a respective aperture (46) in the casing (30). Each aperture (46) in the casing (30) has an elongate shape in cross-section and each aperture (46) has a bush (120) arranged within the aperture (46) and around the spindle (60) to fill the elongate shaped aperture (46).