Patent ID: 7225624

Claim:
A gas turbine engine, comprising: a compressor operable to increase the pressure of a working fluid; a combustor in flow communication with at least a portion of the working fluid from said compressor, said combustor discharging a hot exhaust gas flow therefrom; a turbine including a rotatable structure with a plurality of turbine blades disposed in flow communication with the hot exhaust gas flow from said combustor, said rotatable structure includes a turbine disk and a preswirl mini-disk coupled thereto; a mechanical housing surrounding at least a portion of the gas turbine engine; and a pump connected to said preswirl mini-disk and located within said mechanical housing to increase the pressure of a flow of component cooling working fluid from said compressor, said pump having an inlet in flow communication with the flow of component cooling working fluid from said compressor and an outlet in fluid flow communication with an engine component to be cooled, said pump rotates with said rotatable structure to increase the pressure of the component cooling working fluid passed through said outlet.