Patent ID: 8920128

Claim:
A gas turbine engine cooling system for deployment within a gas turbine engine, the gas turbine engine cooling system comprising: an impeller, comprising: an inducer piece; an exducer piece abutting the inducer piece; and a hub formed by the inducer piece and the exducer piece; a plurality of hub bleed air passages each having an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub, the plurality of hub bleed air passages formed in the impeller proximate the interface of the inducer piece and the exducer piece; a central bleed air conduit fluidly coupled to the outlets of the plurality of hub bleed air passages and configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto; at least one internal cavity created within the impeller when the inducer piece and exducer piece are assembled, the plurality of hub bleed air passages extending through the at least one internal cavity; and at least one vortex spoiler tube captured within the at least one internal cavity through which at least one of the hub bleed air passages included within the plurality of hub bleed air passages extends.