Abstract: A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.

Abstract: 12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner core of silicon nitride or silicon carbide; and b) applying a ceramic matrix composite material over substantially all of the inner core.

Abstract: 12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner core of silicon nitride or silicon carbide; and b) applying a ceramic matrix composite material over substantially all of the inner core.

Abstract: A bucket tip clearance control system forms part of a turbomachinery apparatus including a casing, an outer shroud coupled with the casing, and an inner shroud coupled with the outer shroud. The tip clearance control system includes a flow circuit for a thermal medium defining a flow path within the outer shroud. A thermal medium source delivers the thermal medium to the flow circuit in a predefined condition according to operating parameters of the turbomachinery apparatus. The temperature of the outer shroud is controlled according to the predefined condition of the thermal medium. By accurately controlling the temperature of the outer shroud, bucket tip clearance can be controlled and optimized during all of the various operation stages of turbomachinery.

Abstract: A plurality of arcuate, circumferentially extending leaf seal segments form an annular seal spanning between annular sealing surfaces of inner and outer casings of a turbine. The ends of the adjoining seal segments have circumferential gaps to enable circumferential expansion and contraction of the segments. The end of a first segment includes a tab projecting into a recess of a second end of a second segment. Edges of the tab seal against the sealing surfaces of the inner and outer casings have a narrow clearance with opposed edges of the recess. An overlying cover plate spans the joint. Leakage flow is maintained at a minimum because of the reduced gap between the radially spaced edges of the tab and recess, while the seal segments retain the capacity to expand and contract circumferentially.

Abstract: A method of operating a gas turbine having inner and outer shells, with the inner shell being radially movable relative to rotor bucket tip passage in the inner shell for flowing a thermal medium. A pair of passage portions are formed in each of the aft and forward inner shell sections with axially communicating passageways between the passage portions. A thermal medium, preferably from an off-turbine site, is provided for flow through the second-stage aft inner shell section, along axial passageways along the mid-line of the inner shell to a first passage portion of the forward inner shell section. Cross-over paths flow the thermal medium from the first passage portions to second circumferentially extending passage portions of the forward inner shell section, in turn, in communication with axial passageways extending from the forward section to the aft section. A second pair of passage portions flow the thermal medium to an outlet in the aft section.

Abstract: A rig and test program for determining the amount, if any, of contamination that will collect in the passages of a fluid flow system, such as a power plant fluid delivery system to equipment assemblies or sub-assemblies, and for establishing methods and processes for removing contamination therefrom. In the presently proposed embodiment, the rig and test programs are adapted in particular to utilize a high-pressure, high-volume water flush to remove contamination from substantially the entire fluid delivery system, both the quantity of contamination and as disposed or deposited within the system.

Abstract: A bucket tip clearance control system forms part of a turbomachinery apparatus including a casing, an outer shroud coupled with the casing, and an inner shroud coupled with the outer shroud. The tip clearance control system includes a flow circuit for a thermal medium defining a flow path within the outer shroud. A thermal medium source delivers the thermal medium to the flow circuit in a predefined condition according to operating parameters of the turbomachinery apparatus. The temperature of the outer shroud is controlled according to the predefined condition of the thermal medium. By accurately controlling the temperature of the outer shroud, bucket tip clearance can be controlled and optimized during all of the various operation stages of turbomachinery.

Abstract: A procedure and tools for quantifying surface cleanliness are described. Cleanliness of a target surface is quantified by wiping a prescribed area of the surface with a flexible, bright white cloth swatch, preferably mounted on a special tool. The cloth picks up a substantial amount of any particulate surface contamination. The amount of contamination is determined by measuring the reflectivity loss of the cloth before and after wiping on the contaminated system and comparing that loss to a previous calibration with similar contamination. In the alternative, a visual comparison of the contaminated cloth to a contamination key provides an indication of the surface cleanliness.

Abstract: A procedure and tools for quantifying surface cleanliness are described. Cleanliness of a target surface is quantified by wiping a prescribed area of the surface with a flexible, bright white cloth swatch, preferably mounted on a special tool. The cloth picks up a substantial amount of any particulate surface contamination. The amount of contamination is determined by measuring the reflectivity loss of the cloth before and after wiping on the contaminated system and comparing that loss to a previous calibration with similar contamination. In the alternative, a visual comparison of the contaminated cloth to a contamination key provides an indication of the surface cleanliness.

Abstract: A procedure and tools for quantifying surface cleanliness are described. Cleanliness of a target surface is quantified by wiping a prescribed area of the surface with a flexible, bright white cloth swatch, preferably mounted on a special tool. The cloth picks up a substantial amount of any particulate surface contamination. The amount of contamination is determined by measuring the reflectivity loss of the cloth before and after wiping on the contaminated system and comparing that loss to a previous calibration with similar contamination. In the alternative, a visual comparison of the contaminated cloth to a contamination key provides an indication of the surface cleanliness.

Abstract: A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in communication with a cavity within the inner barrel in which the flanges of the turbine and compressor rotors are secured to one another. The exit ends of the passages have swirl devices for turning the flow from the general axial direction to a tangential direction corresponding to the direction of rotation of the combined rotors. A leakage seal is provided between the rotor and the stationary component to provide a pressure drop across a plenum and cavity to increase the velocity of air flowing into the cavity. Consequently, cooling air is supplied the cavity at a tangential velocity approaching the rotor velocity with reduced windage and lower temperature, thereby improving the performance of the turbomachinery.