Abstract: A system includes an air cooling system having a heat exchanger, a fan, and a mount. The heat exchanger includes an inlet, an outlet, and a heat exchange conduit between the inlet and the outlet. The inlet is configured to couple to a bleed system of a gas turbine system to extract a bleed flow. The heat exchanger is configured to cool the bleed flow along the heat exchange conduit in a surrounding air to produce a cooled bleed flow. The outlet is configured to couple to a fuel purge system of the gas turbine system to supply the cooled bleed flow as a fuel purge flow. The fan is configured to force an airflow from the surrounding air through the heat exchanger. The mount is configured to mount the air cooling system outside of an enclosure surrounding the gas turbine system.

Abstract: A method includes positioning a braze material along a defect of a component of a turbine system, positioning a cover over the braze material, and focusing a heat source on the cover to melt the braze material along the defect.

Abstract: a tooling assembly for installation relative to a first and second turbomachine component is provided. The tooling assembly includes an axial mounting portion removably couplable to the first turbomachine component. The axial mounting portion includes a first plate, a second plate spaced apart from the first plate, and at least one turnbuckle assembly that extends between, and is coupled to, the first plate and the second plate. At least one of the first plate and the second plate include a radial compression portion. The radial compression portion includes a compression bar radially movable relative to the axial mounting portion and configured to contact the second turbomachine component.

Abstract: An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.

Abstract: A stator vane for a turbomachine is provided. The stator vane includes an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in TABLE I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define suction-side profile sections at each Z value. The suction-side profile sections at the Z values are joined smoothly with one another to form a complete airfoil suction-side shape.

Abstract: A combustor includes an end cover and at least one fuel nozzle extending from the end cover and at least partially surrounded by a combustion liner. The combustor further includes an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extending to the fuel injector. A shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The at least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.

Abstract: A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.

Abstract: A system and method are provided for operating a power generating asset. Accordingly, a plurality of operational data sets are received by a controller. The operational data sets include at least one indication of a performance anomaly. A plurality of predictive models are implemented by the controller to determine a plurality of potential root causes of the performance anomaly and a plurality of corresponding probabilities for each of the potential root causes. A consolidation model is generated for classifying the plurality of potential root causes and corresponding probabilities. The consolidation model is trained via a training data set to correlate the plurality of potential root causes to an actual root cause for the performance anomaly. The consolidation model is implemented by the controller to determine the actual root cause of the performance anomaly based on the plurality of potential root causes and corresponding probabilities.

Abstract: A system and method are provided for reducing vibrations and loads in one or more rotor blades of a wind turbine when the rotor hub is locked against rotation, The method detects that the rotor blades are vibrating above a threshold limit, and determines one or more wind parameters for wind impacting the rotor blades. An initial orientation of the blades is also determined. Based on the wind parameters and initial blade orientation, a first angle of attack for the rotor blades is determined that will reduce the vibrations in the rotor blades. The method then determines if expected loads induced at one or more wind turbine components will exceed a threshold limit at the first angle of attack for the rotor blades. The first angle of attack is modified when the expected loads exceed the threshold limit to reduce the expected loads to below the threshold limit. A controller pitches the rotor blades to achieve the first angle of attack.

Abstract: A sensor interface module for an inspection robot includes a scissor lift for varied radial positioning of, and a universal sensor mount for mounting, a selected one of a plurality of different sensors. A visual inspection module for the robot includes an inspection unit for simultaneously visually inspecting a first surface facing a first direction and a spaced, second surface facing an opposing, second direction toward the first surface. The inspection unit includes a first visual sensor and a second visual sensor, each visual sensor facing in a direction different than the first and second directions. A first reflector reflects an image of the first surface to the first visual sensor, and a second reflector reflects an image of the second surface to the second visual sensor. A robot system may include the sensor interface module and the inspection unit.

Abstract: A method includes routing a combustion gas through a turbine stage along a combustion gas path disposed between a turbine shaft and a turbine casing of a gas turbine, wherein the turbine shaft is disposed along a rotational axis, the turbine casing is disposed circumferentially about the turbine shaft, and the turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The method includes controlling an axial range of different axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion via an isothermal expansion system coupled to the turbine stage in response to a change in a load on the gas turbine.

Abstract: A combustor head end section includes a bundled tube fuel nozzle assembly and an air supply system. The fuel nozzle assembly includes: a forward plate facing a head end air plenum, an aft plate facing a combustion chamber, premixing tubes extending from the forward plate to the aft plate, and a side wall extending circumferentially around the premixing tubes. The forward plate, the aft plate, and the side wall define a fuel plenum, and each premixing tube includes at least one fuel injection hole in fluid communication with the fuel plenum. The air supply system comprises the head end air plenum, a first inlet flow conditioner partially defining the head end air plenum and surrounding the bundled tube fuel nozzle assembly, and a second inlet flow conditioner surrounding the first inlet flow conditioner. The head end air plenum is in fluid communication with a combustion chamber, via the premixing tubes.

Abstract: A method of operating a gas turbine combustor includes: selectively directing fuel and a first air supply through a fuel nozzle assembly in a head end section to produce a first fuel/air mixture, which is ignited within a liner to produce combustion gases; selectively directing a second fuel/air mixture through the liner from at least one first injector disposed at a first axial location; selectively directing a third fuel/air mixture through the liner from at least one second injector disposed at a downstream, second axial location. Each of the fuel nozzle assembly, the first injector(s), and the second injector(s) receives only a respective air supply from a compressor discharge plenum. The second injector(s) receive a respective air supply that is greater than each of the respective air supplies of the fuel nozzle assembly and the first injector(s).

Abstract: A combustor head end section includes an integrated cooling system. The combustor head end section includes: a bundled tube fuel nozzle assembly having a forward plate facing a head end air plenum, an aft plate facing a combustion chamber, and premixing tubes extending from the forward plate to the aft plate. A side wall extends circumferentially around the premixing tubes and extends axially from the forward plate to the aft plate. The forward plate, the aft plate, and the side wall define a fuel plenum, and each premixing tube includes at least one fuel injection hole in fluid communication with the fuel plenum. The head end air plenum is in fluid communication with the combustion chamber, via the premixing tubes. The integrated cooling system comprises an air flow passage integral with an exterior surface of a respective premixing tube and extending from the forward plate to the aft plate.

Abstract: A combustor for a gas turbine engine comprises: a head end section defining a head end plenum and containing a fuel nozzle assembly; and a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein. First injectors, disposed at a first axial location, direct a first fuel/air mixture through the liner. Second injectors, disposed at a different, second axial location, direct a second fuel/air mixture through the liner. Each of the head end section, the first injectors, and the second injectors receives a respective air supply from a compressor discharge plenum that at least partially surrounds the combustor. The respective air supplies are directed to only one of the fuel nozzle assembly, the first injectors, and the second injectors. The first injectors and the second injectors receive more than 50% of the air supply from the compressor discharge plenum.

Abstract: A bundled tube fuel nozzle assembly for a gas turbine combustor includes: a forward plate facing a head end air plenum, an aft plate facing a combustion chamber, and premixing tubes extending from the forward plate to the aft plate. An interior side wall extends circumferentially around the first plurality of premixing tubes and defines an interior fuel plenum, and an exterior side wall extends circumferentially around the interior side wall and defines an exterior fuel plenum. Both side walls extend axially from the forward plate to the aft plate. The interior fuel plenum is in fluid communication with the exterior fuel plenum. Each premixing tube includes at least one fuel injection hole therethrough, which is in fluid communication with the interior fuel plenum. The head end air plenum is in fluid communication with the combustion chamber, via inlet ends of the premixing tubes.

Abstract: A combustor for a gas turbine engine includes a head end section containing a fuel nozzle assembly and a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein. First injectors, disposed at a first axial location, directs a first fuel/air mixture through the liner. Second injectors, disposed at a second downstream axial location, direct a second fuel/air mixture through the liner. A compressor discharge casing, which at least partially surrounds the combustor, defines a plenum from which a first air supply is directed only to the first injectors, a second air supply is directed only to the second injectors, and a third air supply is directed only to the head end section. The second air supply is greater than each of the first air supply and the third air supply.

Abstract: A gas turbine engine combustor includes: a head end section containing a fuel nozzle assembly and defining a head end air plenum; and a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein. First injectors are disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner. A dynamics mitigation system includes cold-side resonators disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end. Each resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum. In some embodiments, quarter-wave tube dampers are installed within the fuel nozzle assembly of the head end section.

Abstract: A combined cycle power plant (CCPP) is provided. The CCPP includes a gas turbine that has a compressor section, a combustion section, and a turbine section. The CCPP further includes a heat recovery steam generator (HRSG) that has a first economizer. The HRSG receives a flow of exhaust gas from the turbine section. The HRSG further includes a fuel heating system that has a fuel supply line and a high temperature heat exchanger disposed in thermal communication on the fuel supply line. The fuel supply line is fluidly coupled to the combustion section. The high temperature heat exchanger is fluidly coupled to the first economizer such that the high temperature heat exchanger receives water from the first economizer. The CCPP further includes a feedwater pump that is fluidly coupled to the high temperature heat exchanger.

Abstract: A directional solidification casting method includes fluidly coupling a feed line conduit with a source of molten metal and with a directional solidification mold at a gating. The mold has an interior chamber with a shape of an object to be cast using directional solidification in a growth direction. The feed line conduit is fluidly coupled with the gating in a downward direction oriented at an angle that is closer to the growth direction of the mold than to another direction that is perpendicular to the growth direction of the mold. The method also includes positioning a downstream portion of the feed line conduit below the gating, directing the molten metal into the mold via the feed line conduit, and casting the object in the mold using directional solidification.