GAS TURBINE ENGINE WITH SECONDARY AIR FLOW CIRCUIT

摘要

Gas turbine engines with a secondary air flow circuit are disclosed. The secondary flow circuit is operative to deliver secondary air flow to the impeller for controlling a temperature of a portion of the impeller. The secondary air flow is delivered to the impeller from across a flowpath through a first opening; and one or more walls defining a cavity separate from the flowpath. The one or more walls further have an opening therein configured to supply a 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. A static structure is 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.