Patent ID: 8556573

Claim:
A diffuser for a centrifugal compressor assembly of a gas turbine engine including an impeller, the diffuser comprising: a diffuser case defining a circumferentially extending inlet space surrounding an exit of the impeller, a plurality of vanes defining therebetween a plurality of circumferentially distributed angled diffuser passages for receiving gas flow from the impeller, the inlet space being disposed between the diffuser passages and the impeller, each vane including a respective leading edge adjacent to or located in the inlet space, and each vane having a corresponding bleed port defined in a suction surface thereof within each of the diffuser passages, each said bleed port being disposed downstream of a leading edge of the vane defining the diffuser passage and upstream of a throat of the diffuser passage, the diffuser case including a passive fluid communication defined at least partially through each vane between the corresponding bleed port and the inlet space upstream of the leading edges, such that air bled from each passage downstream of the leading edges through the bleed ports is passively returned back into the gas flow at a point upstream of the bleed port and of the leading edge of the vane by reintroducing the bleed air into the inlet space for recirculation through the diffuser such as to increase a surge margin of the diffuser.