公开(公告)号：EP2855884A4

公开(公告)日：2016-05-11

申请号：EP13797827

申请日：2013-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOSLEY JOHN H ,  ALVANOS IOANNIS ,  STRIPINIS PHILIP S ,  FREIBERG DOUGLAS PAUL ,  PINERO HECTOR M ,  O'CONNOR JOHN J ,  PIETROBON JON

IPC: F02C7/12 ,  F01D5/08 ,  F01D25/08 ,  F01D25/12

CPC classification number: F01D5/082 ,  F01D25/12

Abstract: 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.