IMPELLER-MOUNTED VORTEX SPOILER

The present disclosure is directed to a system (100) for bleeding air from a compressed gas path (42) of a gas turbine engine (10). The system (100) includes an impeller (30) positioned at a downstream end (58) of a compressor (16) in the gas turbine engine (10). The impeller (30) includes an impell...

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Bibliographische Detailangaben
Hauptverfasser:	WASLO, Daniel, RICHARDSON-BACH, Michael
Format:	Patent
Sprache:	eng ; fre ; ger
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 STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present disclosure is directed to a system (100) for bleeding air from a compressed gas path (42) of a gas turbine engine (10). The system (100) includes an impeller (30) positioned at a downstream end (58) of a compressor (16) in the gas turbine engine (10). The impeller (30) includes an impeller hub (50), an impeller arm (52) coupled to the impeller hub (50), and a plurality of circumferentially spaced apart impeller vanes (56) extending radially outwardly from the impeller arm (52). The impeller arm (52) defines an impeller arm aperture (102) extending therethrough. A vortex spoiler (104) is positioned radially inwardly from the impeller arm (52) and defines a vortex spoiler passage (114) extending radially therethrough. Bleed air (108) flows from the compressed gas path (42) radially inwardly through both the impeller arm aperture (102) and the vortex spoiler passage (114).