Patent ID: 8087249

Claim:
A gas turbine engine turbine cooling system comprising: an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller, a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser, one or more channels in fluid communication with the cooling air bleed means, each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section, the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators, and a generally axially aftwardly extending section of each of the one or more channels terminating at an aft conical section including cooling air apertures of an inner combustor casing diverging outwardly with respect to an engine centerline and disposed between the one or more channels and the annular cooling air plenum.