Abstract: A vane assembly for a gas turbine engine which is a single unitary component that includes an aerofoil. A leading edge passageway is disposed proximal to a leading edge of the aerofoil and configured to receive a flow of a fluid therein. The vane assembly further includes a connecting passageway fluidly communicating the leading edge passageway with a trailing edge distribution passageway that is spaced apart from the leading edge, the leading edge passageway and a trailing edge of the aerofoil. The vane assembly further includes a plurality of trailing edge passageways disposed proximal to a pressure surface of the aerofoil and extending from the trailing edge distribution passageway towards the trailing edge along a chordwise direction. Each trailing edge passageway is configured to discharge the fluid through a corresponding passageway outlet disposed on the pressure surface and in fluid communication with a corresponding trailing edge passageway.

Abstract: A gas turbine engine for an aircraft. The gas turbine engine for an aircraft comprising: an engine core comprising an annular gas passage, 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; and a power 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. The engine further has a recirculatory lubricant system which feeds lubricant to and scavenges lubricant from the power gearbox. The engine further has a circumferential row of inlet guide vanes, located downstream of the fan at an air inlet of the annular gas passage. The recirculatory lubricant system includes one or more return passages for lubricant scavenged from the power gearbox, the return passages crossing the annular gas passage through one or more of the inlet guide vanes.

Abstract: A gas turbine engine for an aircraft. The gas turbine engine for an aircraft comprising: an engine core comprising an annular gas passage, 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; and a power 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. The engine further has a recirculatory lubricant system which feeds lubricant to and scavenges lubricant from the power gearbox. The engine further has a circumferential row of inlet guide vanes, located downstream of the fan at an air inlet of the annular gas passage. The recirculatory lubricant system includes one or more return passages for lubricant scavenged from the power gearbox, the return passages crossing the annular gas passage through one or more of the inlet guide vanes.

Abstract: A bearing support structure for a gas turbine engine located within an internal portion of the engine. The bearing support structure has a plurality of stators, a first section, a second section, a first bearing assembly, and a second bearing assembly. The first section depends forwardly from the plurality of stators relative to the longitudinal axis. The section second depends rearwardly from the plurality of stators relative to the longitudinal axis and is detachably mounted to the plurality of stators. The first bearing assembly is supported relative to the plurality of stators by the first section. The second bearing assembly is supported relative to the plurality of stators by the second section. The second section is detachably mounted to the plurality of stators.

Abstract: An apparatus comprising a shaft for a gas turbine engine, the shaft comprising a shaft flange; a turbine rotor for the gas turbine engine, the turbine rotor comprising a turbine rotor flange configured to couple to the shaft flange; and a stub shaft comprising a stub shaft flange configured to couple to the shaft flange. The stub shaft is concentric with the shaft and configured to have a first interference fit around a portion of the turbine rotor.

Abstract: A geared gas turbine engine comprises at least one compressor, at least one turbine, a fan, a gearbox and a support structure. At least one turbine is arranged to drive the fan via the gearbox. The fan is rotatably mounted in the support structure and the support structure supports the gearbox. The support structure includes a stator vane arrangement comprising a plurality of circumferentially spaced stator vanes extending radially between inner and outer annular walls. The inner annular wall has two axially spaced radially inwardly extending annular flanges and a plurality of circumferentially spaced buttresses extending axially between the annular flanges. The outer annular wall has two axially spaced radially outwardly extending annular flanges and a plurality of circumferentially buttresses extending axially between the annular flanges. The flanges and buttresses increase the strength of the support structure to carry the torque loads of the gearbox.

Abstract: Described is an oil distributor comprising: an oil distribution conduit having an inlet end and an outlet; an oil delivery arrangement at the outlet of the oil distribution conduit, the oil delivery arrangement including a circumferential channel having a base, an upstream wall and a downstream delivery wall, wherein the delivery wall includes a plurality of circumferentially distributed delivery apertures extending therethrough.

Abstract: Described is an oil distributor comprising: an oil distribution conduit having an inlet end and an outlet; an oil delivery arrangement at the outlet of the oil distribution conduit, the oil delivery arrangement including a circumferential channel having a base, an upstream wall and a downstream delivery wall, wherein the delivery wall includes a plurality of circumferentially distributed delivery apertures extending therethrough.