Turbine engine with induced pre-swirl at the compressor inlet

Details Turbine engine with induced pre-swirl at the compressor inlet Turbine engine with induced pre-swirl at the compressor inlet

F - Mech Eng,Light,Heat,Weapons

01

D

60/183

F01D 1/12 (2006.01) F04D 27/02 (2006.01)

Patent

CA 1317467

Abstract of the Disclosure A jet flap construction for the compressor of an aircraft gas turbine engine provided with a bleed means for bleeding air interstage of the compressor and communicating with the hollowed-out struts in the air- flow path to the compressor. The hollow struts are each provided with one or more rows of discrete open- ings extending from the shroud to the hub on the strut to form an aligned series of jets for discharging the pressurized bleed air and forming a jet flap, thereby providing pre-swirl at the compressor inlet.

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