Abstract: A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

Abstract: An improved device and system for facilitating polymerase chain reaction including a light source, detector, waveguide, and filters that occupy minimal space and facilitate detection of stationary samples, reduced sample read time, and simultaneous reading of multiple light wavelengths.

Abstract: A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

Abstract: A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

Abstract: The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle portion is fluidly coupled to a fuel nozzle plenum within the housing body, and the at least one fuel injection lance is fluidly coupled to an injector fuel plenum within the housing body. In some cases, the fuel nozzle portion is a bundled tube fuel nozzle having one or more subsets of tubes. The fuel injection lances are positioned along a radial side of the housing body or circumferentially between two subsets of tubes. Liquid fuel cartridges extend through the fuel nozzle portion, the fuel injection lances, or both.

Abstract: A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.

Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.

Abstract: A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.

Abstract: The present invention relates to polymers and blends of polymers comprising anthracene moieties able to undergo a cycloaddition reaction under certain stimuli, thereby forming polymer adducts endowed with improved or additional properties with respect to those of the starting polymers.

Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.

Abstract: A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.

Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each transition duct includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. Each transition duct further includes an upstream portion and a downstream portion. The turbomachine further includes a late injection assembly disposed between the upstream portion and the downstream portion of a transition duct and which provides fluid communication for an injection fluid to flow into the interior downstream of the inlet of the transition duct. The late injection assembly includes a late injection ring.

Abstract: A turbomachine includes a plurality of transition ducts and a support ring assembly. The outlet of a transition duct includes an inner flange and an outer flange. The turbomachine includes bore holes defined in the inner flange and outer flange, mating bore holes defined in the support ring assembly, and mechanical fasteners connecting the inner flange and the outer flange to the support ring assembly. A first one of the bore holes or mating bore holes has a first maximum radial gap and a first maximum tangential gap relative to an associated mechanical fastener. A second one of the bore holes or mating bore holes has a second maximum radial gap and a second maximum tangential gap relative to an associated mechanical fastener. The second maximum radial gap is greater than the first maximum radial gap or the second maximum tangential gap is greater than the first maximum tangential gap.

Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array and including a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly.

Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. An outlet of each of the plurality of transition ducts is offset from an inlet along the longitudinal axis and the tangential axis. Each of the plurality of transition ducts further includes an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path. The turbomachine further includes a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly. Each of the plurality of support assemblies includes a rod extending between the upstream portion and the support ring assembly.

Abstract: Described herein are poly(aryl ether) (“PAE”) adhesive compositions including at least one PAE chelating agent. The PAE chelating agent is a PAE polymer. In some embodiments, the PAE adhesive composition can optionally include one or more poly(aryl ether ketone) polymers distinct from the PAE chelating agent. The PAE adhesive composition can be incorporated into polymer-metal junctions to improve the strength thereof. In some such embodiments, the adhesive composition can be disposed between a portion of the plastic component and a portion of the metal component of the polymer-metal junction. In some embodiments, the PAE adhesive compositions can be used in conjunction with one or more adhesion promoters distinct from the PAE adhesive composition. In some embodiments, polymer-metal junctions including the PAE chelating agent can be desirably incorporated in mobile electronic device components.

Abstract: The present disclosure is directed to a mounting assembly for a fluid conduit. The mounting assembly includes a casing, a first fluid conduit segment, and a second fluid conduit segment. A fitting is spaced apart from the casing. The fitting couples the first fluid conduit segment and the second fluid conduit segment. A bracket includes a casing mounting portion coupled to the casing, a first fitting mounting portion spaced apart from the casing mounting portion and coupled to the fitting, and a thickness. The thickness of the bracket permits the fitting to move relative to the casing.

Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.

Abstract: A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.