Patent ID: 7708519

Claim:
A vortex spoiler for delivery of a cooling airflow in a turbine engine comprising: a radial exterior sidewall positioned to rotate about an axis of rotation; a radial interior sidewall disposed radially inward of, and surrounded by, the radial exterior sidewall; a core area coupled between the radial exterior sidewall and the radial interior sidewall, the core area extending inwardly perpendicularly to the axis of rotation, the radial exterior sidewall, the radial interior sidewall and the core area defining a discrete vortex spoiler; a plurality of inlet ports formed in and spaced circumferentially about the radial exterior sidewall; a plurality of outlet ports formed in and spaced circumferentially about the radial interior sidewall, the plurality of outlet ports configured to provide an outlet for the cooling airflow from the vortex spoiler; and a plurality of bores extending through the core area coupling each of the plurality of outlet ports to one of the plurality of inlet ports and defining a plurality of ducts that fluidly communicate the inlet ports and the outlet ports, each duct configured such that a cooling airflow may pass radially inwardly with minimal tangential stress and minimal static pressure loss.