Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.

Abstract: The present application provides a sealing assembly for use with a transition piece and a stage one nozzle of a gas turbine engine. The sealing assembly may include a seal element, an overlay piece positioned on the seal element, and a side seal positioned on the overlay piece.

Abstract: The present application provides a seating assembly for use with a transition piece and a stage one nozzle of a gas turbine engine. The seating assembly may include a support member positioned between the transition piece and the stage one nozzle and a primary spring element positioned on the support member and in contact with the stage one nozzle. The primary spring element may include a single bend therein.

Abstract: An injection assembly for use with a combustor is provided. The injection assembly includes an effusion plate that has a plurality of plate openings and a plate sleeve having a sidewall portion that includes a forward edge. The forward edge is coupled to the effusion plate such that the effusion plate is oriented obliquely with respect to a centerline extending through the combustor. The injection assembly also includes a plurality of ring extensions where each of the ring extensions is coupled to one of the plurality of plate openings. Each ring extension extends rearwardly into the plate sleeve.

Abstract: A compliant foil seal comprises a bottom foil configured to be located circumferentially around at least a portion of a rotor, and one or more upper foils configured to cooperate with a stator to position the bottom foil to compliantly face the rotor and be located between the stator and the rotor. A compliant foil seal assembly and a rotary machine are also presented.

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: An apparatus for sealing gas path leakage within a turbomachine is provided. The apparatus may include at least one seal system, which may include at least one sealing shim, at least one spring; and at least one shim protection material. The seal system may be inserted between a first and a second structure of the turbomachine. The seal system may adjust for misalignments between the first and the second structures of the turbomachine.

Abstract: An injection assembly for use with a combustor is provided. The injection assembly includes an effusion plate that has a plurality of plate openings and a plate sleeve having a sidewall portion that includes a forward edge. The forward edge is coupled to the effusion plate such that the effusion plate is oriented obliquely with respect to a centerline extending through the combustor. The injection assembly also includes a plurality of ring extensions where each of the ring extensions is coupled to one of the plurality of plate openings. Each ring extension extends rearwardly into the plate sleeve.

Abstract: An apparatus for providing active clearance control between blade tips and seals in a turbomachine comprising: a first stator carrier segment, with stator seals centripetally disposed on it; a second stator carrier segment located along a same circumference as the first stator carrier segment, also with stator seals centripetally disposed on it; a shell that adjustably houses the first stator carrier segment and the second carrier segment; at least one displacement apparatus in operable communication with at least one stator carrier segment and configured to position the at least one stator carrier segment to provide active clearance control to the stator seals disposed on the at least one stator carrier segment.

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: 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: An apparatus for providing active clearance control between blade tips and seals in a turbomachine comprising: a first stator carrier segment, with stator seals centripetally disposed on it; a second stator carrier segment located along a same circumference as the first stator carrier segment, also with stator seals centripetally disposed on it; a shell that adjustably houses the first stator carrier segment and the second carrier segment; at least one displacement apparatus in operable communication with at least one stator carrier segment and configured to position the at least one stator carrier segment to provide active clearance control to the stator seals disposed on the at least one stator carrier segment.