Compound nozzle cooled engine

Details Compound nozzle cooled engine Compound nozzle cooled engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/16 (2006.01) F01D 5/18 (2006.01) F01D 25/12 (2006.01) F02C 9/18 (2006.01)

Patent

CA 2607878

A gas turbine engine (10) includes a compressor (18), combustor (20), and high pressure turbine (22) operatively joined together. The turbine (22) includes a nozzle (42) followed by a row of rotor blades (50). A first bleed circuit (76) is joined in flow communication between the last stage of the compressor (18) and a forward cooling channel (66) in vanes (44) of the nozzle (42) for feeding first cooling holes (70) therein with pressurized primary air at a first pressure. A second bleed circuit (78) is joined in flow communication between an intermediate stage of the compressor (18) and aft cooling channels (68) in the nozzle vanes (44) to feed second cooling holes (72) with pressurized secondary air at a second pressure less than the first pressure.

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