Abstract: Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.

Abstract: Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.

Abstract: A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.

Abstract: A method and system for controlling the clearance in a gas turbine. The current clearance between a turbine blade and a casing of the gas turbine is determined. Then, a determination is made as to whether the current clearance is within a predetermined clearance threshold and a control action is taken if the current clearance is outside of the predetermined clearance threshold.

Abstract: A closed loop inner shroud assembly for a gas turbine. The shroud assembly may include a shroud body, a cover plate, an inlet though the cover plate to the shroud body, a serpentine passageway through the shroud body, and an outlet from the shroud body to the cover plate.

Abstract: A sealing arrangement for the post impingement cavity of a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine energy efficiency. The stator shroud segment includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds, each having a leading edge hook and a trailing edge hook. The leading and trailing hooks of each of the inner shrouds are respectively engaged with the leading and trailing edge grooves of the outer shroud so as to connect the inner shroud to the outer shroud. The resilient shaped seal is located at a trailing edge of the respectively engaged inner and outer shrouds at an interface of the inner shroud and the outer shroud. In an example embodiment, a sealing groove is defined in the outer shroud for receiving the aft resilient seal.

Abstract: Angel wing seals for turbines are described. In one aspect, an angel wing seal between a rotor blade and nozzle in a turbine inhibits ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces. The seal includes, in an example embodiment, a seal body extending from a shank of the blade and generally toward the nozzle. The seal body has at least one concave surface.

Abstract: An active clearance control system is provided that uses compressor extraction air to manipulate blade tip clearance in an industrial gas turbine and compressor. A stream of air is taken from a cooling and sealing air circuit and redirected to be used for active clearance control. The spent clearance control air is re-introduced into the hot gas path of the gas turbine for cooling and sealing purposes.

Abstract: An inner shroud assembly for a turbine comprising a plurality of part-annular segments combining to form an inner, annular shroud adapted to surround rotating components of a turbine, each segment having a pair of end faces that are juxtaposed similar end faces on adjacent segments with gaps therebetween; at least one convection cooling hole in the segment, opening along at least one of the pair of end faces. The cooling hole opens specifically into a diffuser recess formed in one of the pair of end faces for diffusing the flow of cooling air into the gap.

Abstract: An inner shroud assembly for a turbine comprising a plurality of part-annular segments combining to form an inner, annular shroud adapted to surround rotating components of a turbine, each segment having a pair of end faces that are juxtaposed similar end faces on adjacent segments with gaps therebetween; at least one convection cooling hole in the segment, opening along at least one of the pair of end faces. The cooling hole opens specifically into a diffuser recess formed in one of the pair of end faces for diffusing the flow of cooling air into the gap.