Abstract: A gas turbine engine cooling airflow pickup and delivery system which radially inwardly traverses the torque transmittal path of the compressor section at a relatively large radius location, then extends substantially farther inwardly to a significantly smaller radius location, all with minimal static pressure loss to the cooling airflow. Pressurized, substantially non-swirling air from the compressor stage is supplied to a collector, and from the collector thru pickup holes arranged at an angle of 45 degrees reversely to the direction of rotation of the shaft. The pressurized air is then lead into a vortex spoiler which has a plurality of blades smoothly curved reversely to the direction of rotation of the shaft, the radially outer end of each blade being inclined in matching relation to the pickup holes.

Abstract: A rotor assembly for a gas turbine engine has a disc with dovetail grooves and a plurality of blades with dovetail roots contoured to be received within the grooves. The inner surface of a flexible, high temperature, low compression set seal is bonded to the inner surface of each root portion. The outer surface of the seal has two portions inclined at an angle and spaced apart to define a surface portion for sealingly contacting the base of the groove. The longitudinal edges of the outer surface are curved to facilitate assembly.