Patent ID: 9228497
Filing Date: 2016-01-05
CPC Classification: F01D,F02C,F04D,Y02T

Claim Text:
1. A gas turbine engine, comprising: a compressor having an impeller; a diffuser having a plurality of diffuser vanes; wherein the impeller is a centrifugal impeller, and wherein the diffuser is a radial diffuser; wherein the diffuser forms a flowpath downstream of the impeller; wherein the diffuser vanes extend across the flowpath; and wherein at least one of the diffuser vanes has a first opening extending through the diffuser vanes and across the flowpath; a combustor in fluid communication with the compressor; a turbine in fluid communication with the combustor; and a secondary flow circuit operative to deliver secondary air flow to the impeller for controlling a temperature of a portion of the impeller, wherein the secondary air flow is delivered to the impeller from across the flowpath through the first opening; and one or more walls defining a cavity separate from the flowpath, the one or more walls further having an opening therein configured to supply the secondary air flow from the cavity to at least one diffuser vane, wherein the impeller includes a plurality of blades and a back face opposite the plurality of blades, further comprising a static structure spaced apart from the back face and configured to direct the secondary air flow from a radially outer tip portion of the impeller radially inward along the back face of the impeller.