Abstract: A seal assembly includes an annular hanger having a supporting ledge. An arcuate seal segment includes an outer rail mounted on the ledge and supporting an inner seal. An arcuate carrier is mounted between the hanger and the rail, and includes a piston mounted in a bore. The bore is selectively pressurized to deploy the piston between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a seal assembly including a brush seal and a plurality of seal bristles to a first rotatable shaft, and positioning the seal assembly such that the seal bristles contact a second rotatable shaft to facilitate sealing between the first and second rotatable shafts during gas turbine engine operation.

Abstract: Multistage brush seals are made by initially specifying designs thereof for collectively sharing a differential pressure along an adjacent land subject to relative rotation with the seals. The seals are modified to share the loading without blowdown therefrom. The seals are further modified to ensure rotational stability with the land. The seals are built and tested under pressure to determine pressure blowdown thereof. And then, the seals are again modified to share the pressure loading under blowdown. In this way, the seals share the load in situ under the effects of blowdown.

Abstract: One embodiment of the present invention comprises an actuating mechanism for a turbine comprising a compliant member (meaning at least one compliant member) comprising a series of serpentine folds forming a plurality of fold sections and a central cavity (meaning at least one central cavity) interposed between the adjacent fold sections wherein the compliant member is movable between a first retracted position and a second extended position upon introduction of a pressurized medium into the central cavity and dispersion of the pressurized medium within the serpentine folds.

Abstract: Respective combustion gas streams are generated in a can combustor. The streams are channeled downstream into an annular turbine nozzle. And, dynamic interaction of circumferentially adjacent combustion gas streams is suppressed axially between the cans and the nozzle.

Abstract: An actuated seal assembly for controlling flow in a fluid path in turbomachinery comprising a seal and a seal carrier coupled to the seal is provided. A displacement apparatus is coupled to the seal carrier for positioning the seal so as to control the flow in the fluid path. In addition, a drive system is provided for powering the displacement apparatus.

Abstract: A seal assembly includes an annular hanger having a supporting ledge. An arcuate seal segment includes an outer rail mounted on the ledge and supporting an inner seal. An arcuate carrier is mounted between the hanger and the rail, and includes a piston mounted in a bore. The bore is selectively pressurized to deploy the piston between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component.

Abstract: Respective combustion gas streams are generated in a can combustor. The streams are channeled downstream into an annular turbine nozzle. And, dynamic interaction of circumferentially adjacent combustion gas streams is suppressed axially between the cans and the nozzle.

Abstract: Multistage brush seals are made by initially specifying designs thereof for collectively sharing a differential pressure along an adjacent land subject to relative rotation with the seals. The seals are modified to share the loading without blowdown therefrom. The seals are further modified to ensure rotational stability with the land. The seals are built and tested under pressure to determine pressure blowdown thereof. And then, the seals are again modified to share the pressure loading under blowdown. In this way, the seals share the load in situ under the effects of blowdown.

Abstract: A brush seal assembly that in an exemplary embodiment includes an elongate brush core holder, at least three elongate brush core packs bundled together side-by-side in the brush core holder forming a single assembly. Each brush core pack includes a bristle holder and a plurality of bristles coupled to the bristle holder.

Abstract: A brush seal assembly that in an exemplary embodiment includes an elongate brush core holder, at least three elongate brush core packs bundled together side-by-side in the brush core holder forming a single assembly. Each brush core pack includes a bristle holder and a plurality of bristles coupled to the bristle holder.

Abstract: A method of retrofitting a gas turbine wherein the gas turbine comprises a stator and a rotor. The rotor is coaxially aligned with the stator and spaced apart from the stator so as to define a gap therebetween. The method of retrofitting comprises fixedly securing a sealing member to the stator. The sealing member is configured to restrict a flow of a fluid medium in a fluid path across the gap and generate a pressure drop generally transverse to the gap during operation of the gas turbine.

Abstract: The present invention provides an actuated seal assembly for controlling flow in a fluid path in turbomachinery comprising a seal and a seal carrier coupled to the seal. A displacement apparatus is coupled to the seal carrier for positioning the seal so as to control the flow in the fluid path. In addition, a drive system is provided for powering the displacement apparatus.

Abstract: A method of retrofitting a gas turbine wherein the gas turbine comprises a stator and a rotor. The rotor is coaxially aligned with the stator and spaced apart from the stator so as to define a gap therebetween. The method of retrofitting comprises fixedly securing a sealing member to the stator. The sealing member is configured to restrict a flow of a fluid medium in a fluid path across the gap and generate a pressure drop generally transverse to the gap during operation of the gas turbine.

Abstract: One embodiment of the present invention comprises an actuating mechanism for a turbine comprising a compliant member (meaning at least one compliant member) comprising a series of serpentine folds forming a plurality of fold sections and a central cavity (meaning at least one central cavity) interposed between the adjacent fold sections wherein the compliant member is movable between a first retracted position and a second extended position upon introduction of a pressurized medium into the central cavity and dispersion of the pressurized medium within the serpentine folds.

Abstract: A brush seal is provided between a first stationary component and a second rotating component. A cooling medium is provided through a plurality of jet nozzles for flow along an upstream surface portion of the brush seal bristles and along the rotating component surface adjoining the tips of the bristles. The cooling medium cools the brush seal bristles to a temperature below the temperature of the working fluid passing through the turbine. The jet nozzles may be arranged in the shroud or in the upstream backing plate of the brush seal to direct the cooling medium toward the juncture of the brush seal and the sealing surface.

Abstract: An embodiment providing a seal assembly for turbomachinery for controlling flow of a fluid medium in a fluid path comprises a casing having an internal pressure load path and a seal carrier chamber. A movable seal carrier is disposed within the seal carrier chamber and interposed between the pressure load path and an external flow path. In addition, a pressure selecting apparatus is coupled to the pressure load path to control flow therethrough. Moreover, the position of the movable seal carrier moves in response to a pressure differential determined by the pressure selecting apparatus between the pressure load path and the external flow path.

Abstract: One method empirically determines a stiffness value for each of two or more different subsets of the bristles of a brush seal, then calculates a variation in stiffness, and then identifies the brush seal as defective if the calculated variation in stiffness exceeds a predetermined stiffness variation criteria. One apparatus includes a load transducer having a contact head sized to contact less than twenty percent of the bristles, a displacement transducer which measures the displacement of the free ends of the contacted bristles, and a clamp for securing the brush seal and presenting the bristles for contact.

Abstract: A brush seal is comprised of arcuate seal segments having ends cut in a radial direction with bristles “canted” at an approximate 45° angle relative to radii of the segments, leaving triangular regions adjacent one end of each segment devoid of bristles at the segment interfaces. The brush seals are retrofit into conventional labyrinth seals with the backing plate for the bristles comprising a labyrinth tooth profile extending fully 360° about the seal, including those areas where bristles are not present. The sealing capacity is not substantially degraded, while affording significant sealing improvements over conventional labyrinth seals. Additionally, when retrofit into labyrinth seals with radial movement, the individual labyrinth seal segments are free to move radially independently of one another during transients.

Abstract: The positions of brush seal segments are positively adjusted relative to a housing carrying the brush seal segments and the opposing sealing component by employing members formed of thermally responsive material. The members are heated by heating elements receiving controlled power. By increasing or decreasing the power provided to the heating elements, the members are expanded or contracted to move the brush seal segments toward or away from the opposing sealing component.