Abstract: A support arrangement for a brush seal positioned between a stationary and a rotatable component of a turbomachine. The brush seal has a downstream backing plate that includes an axially-extending lip adjacent its radially outermost end to minimize axial deflection of the seal as a result of a gas pressure differential acting across the seal.

Abstract: A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annular row of identical first and second flow passages with first and second inlets respectively and outlets. First and second flow means direct first and second portions of the flow to the first and second flow passages, respectively. A valve is used for selectively modulating the second portion of the flow which together with a controller may be used for selectively preventing the second portion of flow from flowing through the second flow passages during a first cruise of engine operation and allowing substantially unrestricted flow therethrough during a takeoff mode of engine operation. The second flow means preferably includes an inducer manifold disposed between the valve and the second inlets.

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.