To reduce pressurized air extracted from a compressor for cooling a turbine component.
A gas turbine engine includes: a multistage axial compressor; an annular combustor 20 for mixing fuel with the pressurized air 34 to generate a combustion gas 38; and a high pressure (HP) turbine 22 including a row of HP turbine blades 44 having dovetails mounted in dovetail slots 52 in the perimeter of a supporting HP rotor disk 46 joined to compressor blades. The HP disk 46 includes a web 60 extending inwardly from the perimeter with a forward face 50, and a forward seal plate 56 extending radially along the forward face 50 to define an annular manifold 58 in flow communication with the dovetail slot 52, and has an interstage cooling circuit 48 joined in flow communication from an intermediate stage of the compressor to the disk forward face 50 for channeling interstage bleed cooling air 34b thereto.
MONIZ THOMAS ORY
ORLANDO ROBERT JOSEPH
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Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka