Abstract: Turbine cooling systems and methods are disclosed herein. The turbine cooling system may include a rotor disk having a bucket attached thereto. The bucket may include a shank cavity. The turbine cooling system may also include a cover plate positioned at least partially about the rotor disk and the shank cavity. The cover plate may be configured to separate a first flow of cooling fluid from a second flow of cooling fluid. At least one aperture may be disposed in the cover plate about the shank cavity. The at least one aperture may be configured to provide the first flow of cooling fluid to the shank cavity.

Abstract: A turbomachine seal assembly includes a rotor disposed about an axial centerline, the rotor having an outer surface. Also included is a stationary component extending circumferentially about the rotor. Further included is at least one primary annular seal ring operably coupled to the stationary component and extending radially inwardly to close proximity with the outer surface of the rotor. Yet further included is a secondary annular seal ring operably coupled to the stationary component and integrally formed with the at least one primary annular seal ring, the secondary annular seal ring extending radially inwardly to close proximity with the outer surface of the rotor.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the sealing device segments includes a stator interface element, a shoe plate having an extended portion having one or more labyrinth teeth facing the rotor and a load bearing portion, wherein the shoe plate is configured to generate an aerodynamic force between the shoe plate and the rotor. The sealing device segment further includes a secondary seal configured to be in contact with the stator interface element at a radially outer end and configured to be in contact with an elevated nose section of the extended portion of the shoe plate on a radially inner end; and multiple flexible elements attached to the shoe plate and to the stator interface element.

Abstract: According to one aspect of the invention, a method for temperature control of a turbine engine compressor includes directing a fluid from a first region proximate a main flow path in a downstream portion of a structure in a compressor to an upstream portion of the structure, wherein the fluid is cooled as the fluid flows through the upstream portion of the structure. The method further includes directing the fluid from the upstream portion of the structure downstream to a second region of the compressor to cool the second region, wherein the fluid is directed through passages in the upstream and downstream portions of the structure thereby substantially conserving an energy of the fluid within the structure and wherein a pressure of the second region is less than a pressure of the first region.

Abstract: An assembly is disclosed that includes a first rotating component and a second rotating component disposed adjacent to the first rotating component. An annular slot may be defined between the first and second rotating components and may include a sealing surface. Additionally, a seal may be disposed within the annular slot and may be configured to be engaged against the sealing surface when the first and second rotating components are rotated. Moreover, the seal may form a non-continuous ring within the annular slot when the seal is engaged against the sealing surface.