Cool tip combustor

Details Cool tip combustor Cool tip combustor

F - Mech Eng,Light,Heat,Weapons

01

D

170/71

F01D 5/08 (2006.01) F01D 5/18 (2006.01) F01D 9/02 (2006.01) F23R 3/06 (2006.01)

Patent

CA 1194803

Abstract A gas turbine engine is provided with a means for cooling tips of turbine blades in a hot turbine section of the engine. Inlet air holds are provided in a radially outer wall section of the combustor, just upstream of a turbine nozzle. Cooling air flows through these inlet air holes, into annulus regions protected from combustion gases, and then downstream along a radially outer wall of the turbine. The cooling air forms a film that cools the turbine blade tips in a localized manner that adds to total engine power output.

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