Arrangements for guiding bleed air in a gas turbine engine

In order to guide air into a bleed arrangement in a gas turbine engine compressor, a support member 23, for a stator vane 20 having an aerofoil 34, is provided with inclined regions 46, 48 which may guide air into a bleed aperture defined by recesses 38, 40. In an alternative arrangement (fig. 6), a...

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Bibliographische Detailangaben
Hauptverfasser:	GARY PETER AUSTIN, CZESLAW PALUSZKIEWICZ, BENJAMIN ALEC LEISHMAN, NICHOLAS ALEXANDER CUMPSTY
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	In order to guide air into a bleed arrangement in a gas turbine engine compressor, a support member 23, for a stator vane 20 having an aerofoil 34, is provided with inclined regions 46, 48 which may guide air into a bleed aperture defined by recesses 38, 40. In an alternative arrangement (fig. 6), a bleed aperture (28) is located axially between an array of stator vanes and a bladed rotor, the rotor blades being surrounded by a surface (66) that has a smaller radius than the engine axis than an annular surface (73) of a support arrangement surrounding the stator vanes, whereby an annular step (78) is defined, the support surface being provided with ramps (62) (63, fig. 7) to guide air into the bleed arrangement. In modifications of this arrangement (figs. 8 - 10), vane supporting platforms may be provided with recesses that cooperate with the recesses of adjacent platforms to define bleed apertures into which air is guided by the ramps.