Abstract: A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a generally bar-shaped damping member loosely arranged in the damper pocket having at least one scrubbing surface, and at least one retainer pin for retaining the bar-shaped damping member in the damper pocket. The bar-shaped damping member is slidably displaceable and rotatable within the damper pocket during rotation of the rotor. The damper pocket in the platform portion has a rear surface with an upper portion and a lower portion at an angle to the upper portion, a pair of spaced side surfaces, and a pair of spaced lower surfaces extending from the rear surface lower portion which are substantially coplanar.

Abstract: A seal assembly positioned between forward and aft rotor stages of a turbine separates a forward cavity and an aft cavity on each side thereof. The seal assembly includes a seal body connected to a platform portion of a stator nozzle located between the forward and aft rotor stages, wherein an inner seal cavity in flow communication with an insert in the stator nozzle is formed therebetween. A static seal member is arranged in sealing relationship with a rotary toothed member between the forward and aft cavities, with the static seal member being connected to the seal body. An intermediate member is positioned between the seal body and the static seal member to define a plenum therebetween in flow communication with the inner seal cavity, the intermediate member having a plurality of angled passages formed therein in which a first end thereof is in flow communication with the plenum and a second end thereof is in flow communication with the aft cavity.

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.