公开(公告)号：EP2971673A4

公开(公告)日：2016-11-09

申请号：EP14774334

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOSLEY JOHN H ,  CHRISIKOS JAMES P ,  GATES ROGER ,  O'CONNOR JOHN J ,  WU CHARLES C ,  GLASSPOOLE DAVID

IPC: F01D5/08

CPC classification number: F02C9/18 ,  F01D5/082 ,  F02C7/18 ,  F05D2220/3215 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

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.