Patent ID: 9677475
Date: 2017-06-13
CPC Classifications: F01D,F02C,F05D,Y02T

Claim:
1. An engine comprising: a turbine section includes a turbine rotor arranged in a plenum; a compressor section includes a compressor rotor assembly having spaced apart inner and outer portions that provide a cooling channel that extends axially, compressor blades extending radially outward from the outer portion which provides an inner core flow path, and a rotor spoke configured to receive a first cooling flow and fluidly connecting the outer portion to the cooling channel, the compressor rotor assembly has a coolant exit in fluid communication with the cooling channel, the compressor rotor assembly configured to communicate the first cooling flow to the turbine rotor; a bleed source configured to provide a second cooling flow; a combustor section includes a tangential onboard injector in fluid communication with the bleed source, the tangential onboard injector configured to communicate the second cooling flow to the turbine rotor; and wherein the compressor rotor assembly has a rotor disk that includes a rotor outer peripheral surface, and wherein the compressor blades are supported on a platform that has a blade inner surface that faces the rotor outer peripheral surface, and wherein the cooling channel is defined between the rotor outer peripheral surface and the blade inner surface.