Patent ID: 6722138
Filing Date: 2004-04-20
Classification: F02C,F05D

Abstract:
For a gas turbine engine that includes a high pressure compressor, a high pressure turbine driving said high pressure compressor and a high pressure vane, static support structure supporting said vane ahead of the high pressure turbine, said compressor including a hub and a seal operatively connected to said hub for sealing the engine's gases from leaking, said vane including a platform having an aft end relative to the flow of the turbine engine's working medium, a portion of compressor air leaking from said high pressure compressor and a portion the cooling air being discharged from the compressor being routed to cool said static support structure, and a portion of said air leaking from said high pressure compressor and a portion the cooling air being discharged from the compressor routed through said support structure to the aft end of said platform before being discharged into the turbine engine's working medium, wherein said vane includes a rear foot supported in a cavity formed in said support structure and said rear foot and said support structure defining a manifold and said portion of said air leaking from said high pressure compressor and said portion the cooling air being discharged from the compressor being routed into said manifold before being routed to said aft end of said platform.