Abstract: A nosecone for a ducted fan gas turbine engine is shown. The nosecone includes a body with an outer surface that tapers in axial extent from an apex to a base of the body, the apex defining a position of 0 percent axial extent and the base defining a position of 100 percent axial extent, and in which the outer surface includes a plurality of undulations extending between a first location on the outer surface and a second location on the outer surface, wherein the first location is positioned at from 0 to 50 percent of axial extent and the second location is positioned at from 85 to 100 percent of axial extent.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid coupled to the coupling portion. The outer lid includes a leading edge, a trailing edge, and a main portion including an outer radial surface. The outer lid further includes a protruding portion connected to the main portion and extending radially outwardly from the main portion. The protruding portion is axially disposed between and spaced apart from the leading edge and the trailing edge. The protruding portion includes a protruding surface contiguous with and extending radially outwardly from the outer radial surface, such that the protruding surface is configured to redirect air drawn through the gas turbine engine.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid. The outer lid includes a leading edge, a trailing edge, a pair of longitudinal edges, and an outer radial surface. Each longitudinal edge includes a first edge portion and a second edge portion. At least one longitudinal edge includes a recessed portion that extends at least axially between the first edge portion and the second edge portion, such that the recessed portion connects the first edge portion to the second edge portion. The recessed portion further extends circumferentially inwards from each of the first edge portion and the second edge portion towards the other longitudinal edge.

Abstract: An annulus filler of a gas turbine engine includes an outer lid including a leading edge, a trailing edge, a first longitudinal edge, a second longitudinal edge, and an outer radial surface. The outer radial surface includes a first nominal surface portion and a second nominal surface portion. The outer radial surface further includes a protruding surface portion extending radially outwardly from each of the first nominal surface portion and the second nominal surface portion and a recessed surface portion extending radially inwardly from each of the first nominal surface portion and the second nominal surface portion. Each of the protruding surface portion and the recessed surface portion is configured to redirect an air drawn through the gas turbine engine.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid. The outer lid includes a leading edge, a trailing edge, a pair of longitudinal edges, and an outer radial surface. Each longitudinal edge includes a first edge portion and a second edge portion. At least one longitudinal edge includes a recessed portion that extends at least axially between the first edge portion and the second edge portion, such that the recessed portion connects the first edge portion to the second edge portion. The recessed portion further extends circumferentially inwards from each of the first edge portion and the second edge portion towards the other longitudinal edge.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine includes a coupling portion and an outer lid coupled to the coupling portion. The outer lid includes a leading edge, a trailing edge, and a main portion including an outer radial surface. The outer lid further includes a protruding portion connected to the main portion and extending radially outwardly from the main portion. The protruding portion is axially disposed between and spaced apart from the leading edge and the trailing edge. The protruding portion includes a protruding surface contiguous with and extending radially outwardly from the outer radial surface, such that the protruding surface is configured to redirect air drawn through the gas turbine engine.

Abstract: A fan unit for a turbofan engine includes a plurality of fan blades mounted to a fan disc unit and a plurality of vortex-generating elements each of which is arranged to generate a respective vortex extending axially between a respective pair of adjacent fan blades during rotation of the fan unit about its rotation axis. During operation of a turbofan engine comprising the fan unit, fan-wake-induced mechanical degradation of compressor blades in a compressor downstream of the fan unit is eliminated, or the rate at which such degradation occurs is reduced.

Abstract: This disclosure concerns aerofoils for an axial flow compressor. The compressor has an array of aerofoils angularly spaced about its axis of rotation. The aerofoils have leading and trailing edges extending in a direction spanning a flow region defined between a radially inner rotor component and a radially outer casing. Each aerofoil has opposing pressure and suction surfaces extending between the leading and trailing edges and terminating at a free end of the aerofoil. Each aerofoil leans towards the pressure surface by an angle of between 10° and 80° in the vicinity of the aerofoil tip. The aggressive negative lean towards the tip may help reduce over-tip leakage flow in use.