Abstract: A turbomachine includes a compressor, a combustor, and a turbine. The turbine includes a nozzle, a shroud, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform, an outer platform spaced apart from the inner platform along a radial direction, and an airfoil extending therebetween. The outer platform extends axially between a forward sidewall and an aft sidewall. The nozzle also includes an aft hook radially outward of the outer platform and axially forward of the aft sidewall of the outer platform. The shroud includes a forward end adjacent to the aft sidewall of the outer platform. A sealing interface is positioned within the cavity, radially outward of the outer platform of the nozzle and axially forward of the aft sidewall of the outer platform of the nozzle.

Abstract: A rotary machine including: a casing providing an annular chamber for rotating components of the machine; a cooling passage extending through the casing or mounted to a surface of casing; a plug assembly connected to the cooling passage and in the casing or mounted to the casing, wherein the plug assembly includes a collar and a conduit aligned with an axis of the collar, and the collar includes a cooling air by-pass passage in fluid communication with the cooling passage such that cooling air from the cooling passage flows through the by-pass passage and returns to the cooling passage, and another cooling passage or a port extending through the conduit of the plug assembly.

Abstract: A sealing assembly for a turbine engine includes a first stationary component. Also included is a second stationary component, wherein the first stationary component and the second stationary component define a gap therebetween. Further included is a discourager seal in contact with at least one of the first stationary component and the second stationary component, the discourager seal having a lip portion disposed within the gap to reduce a fluid flow through the gap.

Abstract: A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a compressor discharge portion, a hot gas path and a first stage nozzle arranged at the hot gas path. A combustor assembly is fluidically connected to the compressor portion. A transition piece has an inlet portion fluidically connected to the combustor assembly and an outlet portion fluidically connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine portion. The seal member extends from a first end to a second, cantilevered end through an intermediate portion including one or more openings that provide a purge fluid flow path from the compressor discharge portion toward the hot gas path.

Abstract: A rotary machine including: a casing providing an annular chamber for rotating components of the machine; a cooling passage extending through the casing or mounted to a surface of casing; a plug assembly connected to the cooling passage and in the casing or mounted to the casing, wherein the plug assembly includes a collar and a conduit aligned with an axis of the collar, and the collar includes a cooling air by-pass passage in fluid communication with the cooling passage such that cooling air from the cooling passage flows through the by-pass passage and returns to the cooling passage, and another cooling passage or a port extending through the conduit of the plug assembly.

Abstract: A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape.

Abstract: A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape.

Abstract: A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at least one rotor disposed in the compression chamber, the at least one stator comprising a stator body having a plurality of tubes for transporting cooling air through passages in the stator body into the compression chamber. The plurality of tubes are surrounded by an air gap for insulating the tubes from the stator body.

Abstract: A compressor case, and an associated method, repaired from damage to a segment of a stator ring hook. Two halves are engaged together at flange faces that define parting lines and that define a hollow interior, the ring hook being located at the interior, compressor case material having been removed at the stator ring hook location and a location of one of the flange faces to provide a space. A patch plug is slid into the space from the one flange face, the shape of the patch plug being complementary to a shape of the missing material space and inter-fitting therein, with an end of the patch plug being located at the one flange face to face an opposed half of the case with the two halves together. A fastener fastens the patch plug to the case and extending from the interior, through the patch plug, to the case.

Abstract: A method and system for regulating a cooling fluid within a turbomachine in real time. The system may an external flow conditioning system for adjusting at least one property of the cooling fluid, wherein the external flow conditioning system comprises an inlet portion and an outlet portion. The system may also include at least one heat exchanger; at least one control valve; at least one bypass orifice; at least one stop valve; and a control system.

Abstract: Embodiments of the present invention provide a system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to a wheelspace area. The system includes a plurality of angular passages that aid in the mixing of a cooling fluid with a working fluid in the wheelspace area.

Abstract: A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to the at least one wheelspace area. The system may also include a plurality of bypass plugs, wherein each of the plurality of bypass plugs is insertable into a bypass chamber opening on each of the plurality of bypass chambers.

Abstract: A compressor case, and an associated method, repaired from damage to a segment of a stator ring hook. Two halves are engaged together at flange faces that define parting lines and that define a hollow interior, the ring hook being located at the interior, compressor case material having been removed at the stator ring hook location and a location of one of the flange faces to provide a space. A patch plug is slid into the space from the one flange face, the shape of the patch plug being complementary to a shape of the missing material space and inter-fitting therein, with an end of the patch plug being located at the one flange face to face an opposed half of the case with the two halves together. A fastener fastens the patch plug to the case and extending from the interior, through the patch plug, to the case.

Abstract: A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at least one rotor disposed in the compression chamber, the at least one stator comprising a stator body having a plurality of tubes for transporting cooling air through passages in the stator body into the compression chamber. The plurality of tubes are surrounded by an air gap for insulating the tubes from the stator body.

Abstract: A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to the at least one wheelspace area. The system may also include a plurality of bypass plugs, wherein each of the plurality of bypass plugs is insertable into a bypass chamber opening on each of the plurality of bypass chambers.

Abstract: A method and system for regulating a cooling fluid within a turbomachine in real time. The system may an external flow conditioning system for adjusting at least one property of the cooling fluid, wherein the external flow conditioning system comprises an inlet portion and an outlet portion. The system may also include at least one heat exchanger; at least one control valve; at least one bypass orifice; at least one stop valve; and a control system.