Abstract: A cooling system for use in a rotor assembly of a gas turbine engine, the rotor assembly including an annular disk rotatable about a centerline axis of the engine and a plurality of blades mounted on the disk. The disk includes alternating posts and slots, with each slot receiving a blade dovetail. The cooling system comprises an axially extending plenum disposed inward of each blade dovetail and a thermal isolation chamber, formed by a seal body, disposed over the outer surface of each disk post. An annular forward blade retainer is attached to the disk and sealed with adjacent structures via inner and outer seals. Alternative structures are disclosed for diverting the cooling air from the plenums, past the inner and outer seals, and into the isolation chambers during operation of the engine so as to cool each disk point, without compromising the structural integrity of the forward blade retainer.

Abstract: A gas turbine rotor blade platform sealing and damping system has elongated symmetrical insert elements of equilateral triangular cross-section loosely received within complementary shaped pockets at the spacing gaps between opposing convex and concave airfoil side edges of adjacently mounted blade platforms. The inserts and pockets are relatively configured to provide self-orientation of the inserts into gap sealing and vibration damping engagement with the platform edges when acted upon by centrifugal force due to rotor rotation. The convex platform edge is thickened at the point of closest proximity with the convex side of the airfoil. Alternative embodiments utilize insert grooves for increased leakage of cooling gas past the platform edges and incorporate a central bore for mass reduction.