Patent ID: 9726032
Date: 2017-08-08
CPC Classifications: F01D,F02C,F04D,F05D,Y10T

Claim:
1. A gas turbine engine comprising: a compressor assembly rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller; a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from the centrifugal impeller, the radial diffuser assembly having a first arcuate wall and a second wall; another diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly; a gas seal coupled between the second wall and a wall of the another diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the another diffuser; a bleed slot positioned within the shroud proximate the centrifugal impeller; and a bleed plenum formed in part by a wall of the shroud and by a non-load bearing material that is attached to the radial diffuser assembly and to the shroud via a pair of flanges that are in direct contact with one another, wherein bleed air that passes through the bleed slot passes directly from the centrifugal impeller, through the bleed slot, and into the bleed plenum.