Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.

Abstract: A method and seal assembly for sealing a rotary machine including a rotary component and a stationary component is provided. The method includes providing a plurality of flexible leaf plates in an opening defined between a pair of spaced walls that include an adjustable front wall and an adjustable back wall that is opposed to the front wall. The method also includes adjusting a width of the opening by axially adjusting at least one of the front and back walls with respect to a central rotational axis of the rotary component.

Abstract: A shaft seal assembly between a rotating shaft and a static shell is disclosed. The shaft seal assembly includes a seal housing in mechanical contact with the static shell, at least two rigid members of the seal housing, and a plurality of compliant plate members defining a sealing ring between the static shell and the rotating shaft. The plurality of compliant plate members is disposed between the at least two rigid members and retained within the seal housing by a compressive force between the at least two rigid members.

Abstract: A method for assembling at least one seal assembly to a turbine having a casing extending at least partially around a rotor is provided. The method includes coupling the seal assembly to the casing such that the seal assembly extends into a fluid flow passage defined between the rotor and the casing and coupling at least one spring between the seal assembly and the casing to bias each seal assembly.

Abstract: A method of assembling a seal assembly for a turbine engine is provided, wherein the method includes providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween, and forming at least one recess within at least one of the outer ring portion and the neck portion. The method also includes extending a biasing mechanism across the seal ring such that the biasing mechanism is positively retained within the at least one recess.

Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.

Abstract: A plurality of arcuate brush seal segments are disposed in radially inwardly opening grooves of a stationary component, enabling tips of the brush bristles to engage the surface of a rotating component. A leaf spring is welded at one end to each brush seal segment and has first and second circumferentially extending curved portions. The first curved portion extends lengthwise of the spring from the welded end to engage the base of the groove at a location intermediate the length of the spring. The second curved portion engages the radial outer face of the segment adjacent the tip of the spring. All of the segments are thus biased for movement radially inwardly toward the rotating component, enabling pressure forces during operation to maintain the brush seal segments properly located to ensure the seal.

Abstract: A plurality of arcuate brush seal segments are disposed in radially inwardly opening grooves of a stationary component, enabling tips of the brush bristles to engage the surface of a rotating component. A leaf spring is welded at one end to each brush seal segment and has first and second circumferentially extending curved portions. The first curved portion extends lengthwise of the spring from the welded end to engage the base of the groove at a location intermediate the length of the spring. The second curved portion engages the radial outer face of the segment adjacent the tip of the spring. All of the segments are thus biased for movement radially inwardly toward the rotating component, enabling pressure forces during operation to maintain the brush seal segments properly located to ensure the seal.

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: 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: In turbomachinery, first and second flowpaths coupled to stages of the compressor flow cooling medium at different temperatures and pressures to components of the turbine. An ejector is provided in the first flowpath for suctioning flow from the second flowpath and combining the two flows for delivery to a component of the turbine at a temperature and pressure intermediate the temperature and pressure of the first and second flows. A flow sensor, flow controller and throttling valve are interposed in the motive flowpath, the exit flowpath or the suction flowpath relative to the ejector for controlling the flow through the ejector.

Abstract: In turbomachinery, first and second flowpaths coupled to stages of the compressor flow cooling medium at different temperatures and pressures to components of the turbine. An ejector is provided in the first flowpath for suctioning flow from the second flowpath and combining the two flows for delivery to a component of the turbine at a temperature and pressure intermediate the temperature and pressure of the first and second flows. A flow sensor, flow controller and throttling valve are interposed in the motive flowpath, the exit flowpath or the suction flowpath relative to the ejector for controlling the flow through the ejector.

Abstract: Leakage flows through seals are used to cool components of a turbine downstream of the seals. At certain seal locations, the leakage flows are restricted to the extent that cooling of downstream components cannot be effected by the leakage flows. The cooling air leakage flow is augmented by extracting bleed air from different stages at different temperatures from a compressor and combining the extracted flows in an ejector to provide a flow having a temperature intermediate the temperatures of the extracted flow streams for augmenting the leakage flow to cool the component. The ejector thus uses high extraction air to entrain lower temperature extraction air to lower the ejector exit air temperature, reducing the magnitude of air required to cool the downstream component and enhancing the effectiveness of the advanced seal.