United Technologies Corporation

Douglas Paul Freiberg

Ioannis Alvanos

Philip S Stripinis

John H Mosley

Hector M Pinero

John J O'Connor

Phililp S Stripinis

Jon Pietrobon

A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

Turbine coolant supply system

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Glastonbury, CT, United States of America

Douglas Paul Freiberg