Abstract: A heat shield panel for a combustor of a gas turbine engine including a panel body having a first surface and a second surface. The second surface being configured to be oriented toward a combustor liner of the combustor. The heat shield further includes a plurality of first pin fins projecting from the second surface of the panel body. Each of the plurality of first pin fins has a rounded top opposite the second surface. The heat shield further includes a plurality of second pin fins projecting from the second surface of the panel body. Each of the plurality of second pin fins has a flat top opposite the second surface. The plurality of second pin fins are intermittently spaced amongst the plurality of first pin fins. The plurality of second pin fins are organized in a uniform distribution across the second surface of the heat shield panel.

Abstract: A heat transfer arrangement includes two or more heat transfer cells. The heat transfer cells together define a boundary between a higher temperature region and a lower temperature region. Each of the two or more heat transfer cells includes two or more walls defining a fluid tight cavity. One or more wick is fused to an inner surface of one or more of the walls to wick liquid from a lower temperature portion of the cavity to a higher temperature portion of the cavity. Combustors having heat transfer arrangements with heat transfer cells and methods of making heat transfer arrangements are also described.

Abstract: A fuel injection assembly includes a fuel injector having end walls spaced apart from one another and side walls extending between the end walls. The end walls and the side walls collectively define a first opening for passage of air. At least one fuel injection member is disposed within the first opening and extends axially between the end walls. The fuel injector terminates at a radially inner surface. A boss that is fixedly connected to the combustion liner and extends radially through the cooling flow annulus to a flange portion positioned at the outer sleeve. The boss defines a second opening that provides for fluid communication between the fuel injector and the second combustion zone. The radially inner surface of the fuel injector is sealingly connected to the flange portion of the boss such that the first opening aligns with the second opening.

Abstract: Disclosed is an inlet system for a gas turbine engine that extends along a longitudinal axial centerline, the inlet system comprising: an inner dome, a shroud located axially aft and radially outward of the inner dome with respect to the centerline, a splitter nose located radially inward of the shroud with respect to the centerline, a first plurality of struts radially disposed between the shroud and the splitter nose with respect to the centerline, a second plurality of struts radially disposed between the splitter nose and a bearing with respect to the centerline, a plurality of inlet guide vanes radially disposed between the splitter nose and the bearing with respect to the centerline, and the plurality of inlet guide vanes axially aft of the plurality of second struts with respect to the centerline.

Abstract: A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.

Abstract: The present disclosure relates to a fuel supply device for gas turbines, and a fuel nozzle and gas turbine having the same. The fuel supply device of present disclosure is mounted to the fuel nozzle for a uniform flow of air introduced thereinto and for allowing uniform mixing with fuel. The present disclosure allows a uniform fuel-air mixture to be supplied to a combustion chamber. According to the present disclosure, it is possible to uniformly supply a fuel-air mixture to a combustion chamber by arranging a plurality of perforated plates in a fuel supply device for gas turbines, to suppress generation of nitrogen oxides, and to prevent flame from stagnating or flowing backward.

Abstract: The method can include, in sequence: varying the flow rate of fuel from the first flow rate to a second flow rate, thereby varying the rotor speed from a first speed to a second speed, varying the flow rate of fuel back to the first flow rate, and rotating the rotor at the first speed for a given period of time.

Abstract: A core duct assembly for a gas turbine engine, the core duct assembly including: a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.

Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The compressor, the combustor, and the turbine are arranged along an extending direction of a rotating shaft. The gas turbine also includes a combustor casing housing the combustor and a turbine casing housing the turbine. The combustor casing and the turbine casing are joined to each other via respective flanges thereof projecting toward the outside. The gas turbine further includes a projection part on an inner face of the combustor casing. The projection part projects toward the inside in a radial direction in at least part of a range in the extending direction of the rotating shaft between the flanges and an end of a combustion chamber on the compressor side in the combustor.

Abstract: A swirler includes a swirler body defining a longitudinal axis. A stack of swirler plates is assembled to the swirler body stacked in a direction along the longitudinal axis. Each of the swirl plates defines a vane portion. The swirler plates are mounted rotated circumferentially about the longitudinal axis relative to neighboring ones of the swirler plates so the vane portions form a swirler vane.

Abstract: A combustor assembly for a gas turbine engine and a method of additively manufacturing the same are provided. A combustor dome includes a combustor wall defining a hole and a circumferential groove defined within the combustor wall around the hole. A floating ferrule assembly is additively manufactured with the combustor dome and includes a ferrule positioned at least partially within the hole and defining a radial lip that is received within the circumferential groove to inseparably position the ferrule within the combustor wall. A build support arm is attached to the ferrule by a frangible connecting member, the frangible connecting member being breakable for separating and removing the build support arm from the ferrule.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Abstract: An evaporative cooling system for a gas turbine includes a first plurality of evaporative cooling media, spaced from the other evaporative cooling media. The system also includes a plurality of valves, with water flowing through at least one valve to fully wet at least one evaporative cooling medium. In one mode of operation, at least one evaporative cooling medium remains dry.

Abstract: A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

Abstract: A fuel supply system for a turbomachine. The supply system includes a starter circuit, at least one first hydraulic resistance and a purge circuit. The purge circuit includes a duct including an opening at the exterior of the supply system. The purge circuit is configured to make purge air flow between a starter injector and the opening through the first hydraulic resistance. The supply system includes a device for measuring a value representative of pressure, which devices are configured to measure a value representative of pressure between the starter injector and the first hydraulic resistance when purge air flows between the starter injector and the first hydraulic resistance.

Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.

Abstract: A fuel injection system may include a fuel spray nozzle including a nozzle head and a nozzle stem. The nozzle head may include an air channel and a swirler in fluid communication with the air channel. The nozzle stem may extend into a compressor discharge pressure cavity and convey fuel to the air channel. The air channel may combine air from the swirler with the fuel from the nozzle stem and convey a mixture of fuel and air to a combustor. The fuel injection system may further include a scoop. The scoop may be coupled to the fuel spray nozzle. The scoop may receive air that flows into the compressor discharge pressure cavity from a diffusor. An outer surface of the fuel spray nozzle and an inner surface of the scoop define a duct in fluid communication with the swirler. The swirler may receive air from the duct.

Abstract: A combined cycle power system includes a gas turbine exhausting an exhaust gas, a heat recovery steam generator including, a first economizer, a first steam generator, a second economizer, a second steam generator, a steam turbine which is driven by the steam generated at the first steam generator and the second steam generator, and a flasher which generates a first flash steam and a first drain water by flashing a portion of the water heated by the first economizer.

Abstract: An additive manufactured article for a gas turbine having a body with two lateral surfaces elongated in a first direction; at least a nested duct housed within the lateral surfaces and elongated in the first direction; a structure so that the nested duct is structurally connected to an attachment within the lateral surfaces, wherein at least the body, the duct and the structure are manufactured by an additive manufacturing process and the structure includes an array of ribs attached to the duct in order to compensate differential elongation along the first direction of the duct with respect to the attachment of the ribs by flexural deformation.