Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The arrangement allows the duct 100 to be axially short.

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

Abstract: The present disclosure relates to a compressor assembly for a gas turbine engine. The compressor assembly comprises a compressor having a compressor stage with a plurality of rotor blades mounted on the rim of a rotor disc within a core air flow path. There is a purge channel extending from a radially inner purge gas source to at least one radially outer outlet at the rim of the compressor stage. The purge channel comprises at least one swirl element and/or at least one orifice for swirling/deflecting a purge gas flowing within the purge channel. In use, a flow of purge gas exits the outlet(s) at least partly in the direction of the core air flow path.

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The arrangement allows the duct 100 to be axially short.

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

Abstract: A diffuser arrangement is provided in which a wall surface of the diffuser arrangement incorporates an upstream part and a downstream part with an aperture between them. There is a step displacement between the upstream part and the downstream part along with specific shaping of the leading edge of the aperture whereby fluid air flow is drawn into the aperture from a fluid flow whilst avoiding undue disturbance to that flow. The present diffuser arrangement allows incorporation within an engine without complex fabrication or structural requirements.

Abstract: A diffuser arrangement is provided in which a wall surface of the diffuser arrangement incorporates an upstream part and a downstream part with an aperture between them. There is a step displacement between the upstream part and the downstream part along with specific shaping of the leading edge of the aperture whereby fluid air flow is drawn into the aperture from a fluid flow whilst avoiding undue disturbance to that flow. The present diffuser arrangement allows incorporation within an engine without complex fabrication or structural requirements.