Patent ID: 7007488

Claim:
A gas turbine engine comprising: a compressor joined to a turbine for being powered thereby; said turbine including a nozzle having a row of hollow vanes extending radially between outer and inner bands, and said outer band is supported in an annular outer casing; each of said vanes having an internal cooling plenum, and a bypass tube extending through said outer and inner bands; a two-ply septum disposed radially between said outer casing and said outer band, and defining independent first and second manifolds; said first manifold surrounding said outer band and disposed in flow communication with said plenums of said vanes; said second manifold surrounding said first manifold and disposed in flow communication with said bypass tubes of said vanes; a bleed circuit disposed in flow communication between said compressor and said first and second manifolds for channeling pressurized air therebetween; and a control valve disposed between said bleed circuit and said first manifold for modulating flow of said pressurized cooling air into said vane plenums.