IMPELLER SHROUD SUPPORTS HAVING MID-IMPELLER BLEED FLOW PASSAGES

Embodiments of an impeller shroud support (40, 110) for disposition around an impeller (30) are provided, as are gas turbine engines (20) including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body (42, 42'), a support arm (44, 44') joined to a...

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Bibliographische Detailangaben
Hauptverfasser:	MANSOUR, Mahmoud, REYNOLDS, Bruce David, BARTON, Michael Todd, HARRISON, Jeffrey D, GAGE, Raymond, KIME, Kent L
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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	Embodiments of an impeller shroud support (40, 110) for disposition around an impeller (30) are provided, as are gas turbine engines (20) including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body (42, 42'), a support arm (44, 44') joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages (54, 54'). Each MIB flow passage includes an inlet (96, 96') in the shroud body and configured to receive bleed air extracted from the impeller, an outlet (100, 100') in the support arm and through which the bleed air is discharged, and a curved intermediate section (98, 98') between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate sections turn the bleed air flowing through the MIB passages in a radially outward direction prior to discharge from the MIB flow passage outlets.