F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/02 (2006.01) F01D 5/04 (2006.01) F02C 6/06 (2006.01) F02C 6/08 (2006.01) F04D 25/16 (2006.01)
Patent
CA 2458550
Air (19, 119) captured from the tips (25, 125) of a compressor (10, 110) of a gas turbine engine is diverted from the engine core (22, 122) and can be collected for auxiliary uses. Gas path separation can be achieved using part-span shrouded compressor blades or using blade tip cut-outs (24) conforming to an airflow dividing annular shroud. In a preferred application for the present invention, the gas turbine engine is the auxiliary power unit of an aircraft.
Selon l'invention, l'air (19, 119) capturé des extrémités (25, 125) d'un compresseur (10, 110) d'un turbine à gaz est dévié du noyau central (22, 122) et peut être recueilli à des fins auxiliaires. Pour séparer la veine gazeuse, on peut utiliser des pales de compresseur carénées sur une partie de l'envergure ou des incisions de bout de pale (24) adaptées à un carénage annulaire servant à diviser l'écoulement de l'air. Dans une application préférée, la turbine à gaz constitue le groupe auxiliaire de bord d'un avion.
Norton Rose Or S.e.n.c.r.l. S.r.l./llp
Pratt & Whitney Canada Corp.
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