Patent ID: 7665310

Claim:
A gas turbine engine comprising: an engine core extending along a core axis; a removable nacelle cowl overlying the engine core, wherein the nacelle cowl has an inner surface facing toward the engine core and an outer surface facing away from the engine core, when the removable nacelle cowl is installed to the engine core; a cooling-air intake structure that receives cooling air through a cooling-air inlet in the nacelle cowl outer surface; a cooling-air delivery duct on the engine core; a cooling-air nacelle-cowl duct directly affixed to and supported on the inner surface of the nacelle cowl, extending from the cooling-air intake structure to a location adjacent to the cooling-air delivery duct; and a nacelle-cowl duct/delivery duct seal between the cooling-air nacelle-cowl duct and the cooling-air delivery duct.