Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.

Abstract: A turbine system is provided. The turbine system includes a compressor configured to compress ambient air and a combustor configured to receive compressed air from the compressor, and to combust a fuel stream to generate an exhaust gas. The turbine system also includes a turbine for receiving the exhaust gas from the combustor to generate electricity; wherein a first portion of the exhaust gas is mixed with the ambient air to form a low-oxygen air stream, and wherein the low-oxygen air stream is compressed using the compressor, and is directed to the combustor for combusting the fuel stream to generate a low-NOx exhaust gas.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.

Abstract: An inlet particle separator system coupled to an engine having an engine exhaust is presented. The inlet particle separator system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The inlet particle separator system further includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Furthermore, the inlet particle separator system includes a fluidic device including a first inlet and an exhaust, where the fluidic device is configured to accelerate the first flow of substantially contaminated air through the scavenge subsystem and emit the first flow of substantially contaminated air via the exhaust of the fluidic device, wherein the exhaust of the fluidic device is different from an exhaust of the engine.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.

Abstract: In certain embodiments, a fuel injector includes a wall separating a fuel passage from an air passage. The fuel injector also includes a fuel injection port extending from a first side of the wall to a second side of the wall for injecting a flow of fuel from the fuel passage into a flow of air in the air passage. In addition, the fuel injector includes first and second feedback lines extending from a downstream end of the fuel injection port to an upstream end of the fuel injection port. The first and second feedback lines are disposed on opposite sides of the fuel injection port. In addition, the first and second feedback lines are disposed entirely within the wall.

Abstract: A power generation system includes a gas turbine system. The turbine system includes a combustion chamber configured to combust a fuel stream a compressor configured to receive a feed oxidant stream and supply a compressed oxidant to the combustion chamber and an expander configured to receive a discharge from the combustion chamber and generate an exhaust comprising carbon dioxide and electrical energy. The system further includes a retrofittable exhaust gas recirculation system including a splitter configured to split the exhaust into a first split stream and a second split stream, a heat recovery steam generator configured to receive the first split stream and generate a cooled first split stream and a purification system configured to receive the first cooled split stream and the second split stream and generate a recycle stream, wherein the recycle stream is mixed with the fresh oxidant to generate the feed oxidant stream.

Abstract: A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.

Abstract: Methods and systems are provided for premixing combustion fuel and air within gas turbines. In one embodiment, a combustor includes an upstream mixing panel configured to direct compressed air and combustion fuel through a premixing zone to form a fuel-air mixture. The combustor also includes a downstream mixing panel configured to mix additional combustion fuel with the fuel-air mixture to form a combustion mixture.

Abstract: A power generation system and method of generating power with reduced NOx emission includes a gas turbine system. The turbine system includes a compressor configured to receive a feed oxidant stream and supply a compressed oxidant stream to a combustion chamber and an expander configured to receive a discharge stream from the combustion chamber and generate an exhaust stream comprising carbon dioxide and electrical energy. The system further includes an exhaust gas recirculation system configured to generate a recycle stream, wherein the recycle stream is mixed with a fresh oxidant to generate the feed oxidant stream. The exhaust gas recirculation system includes an exhaust gas recirculation control loop to control a pilot ratio (diffusion to total fuel ratio) based on received feedback related to combustion parameters. The control loop configured to control the pilot ratio required to keep NOx in its minimum ratios with improved flame stability.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: A trapped vortex combustor includes a trapped vortex cavity having a first surface and a second surface. A plurality of fluidic mixers are disposed circumferentially along the first surface and the second surface of the trapped vortex cavity. At least one fluidic mixer includes a first open end receiving a first fluid stream, a coanda profile in the proximity of the first open end, a fuel plenum to discharge a fuel stream over the coanda profile, and a second open end for receiving the mixture of the first fluid stream and the fuel stream and discharging the mixture of the first fluid stream and the fuel stream in the trapped vortex cavity. The coanda profile is configured to enable attachment of the fuel stream to the coanda profile to form a boundary layer of the fuel stream and, to entrain the incoming first fluid stream to the boundary layer of the fuel stream to form a mixture of the first fluid stream and the fuel stream.

Abstract: In certain embodiments, a fuel injector includes a wall separating a fuel passage from an air passage. The fuel injector also includes a fuel injection port extending from a first side of the wall to a second side of the wall for injecting a flow of fuel from the fuel passage into a flow of air in the air passage. In addition, the fuel injector includes first and second feedback lines extending from a downstream end of the fuel injection port to an upstream end of the fuel injection port. The first and second feedback lines are disposed on opposite sides of the fuel injection port. In addition, the first and second feedback lines are disposed entirely within the wall.

Abstract: A premixing device is provided. The premixing device includes an air inlet configured to introduce compressed air into a mixing chamber of the premixing device and a fuel plenum configured to provide a fuel to the mixing chamber via a circumferential slot and over a pre-determined profile adjacent the fuel plenum, wherein the pre-determined profile facilitates attachment of the fuel to the profile to form a fuel boundary layer and to entrain incoming air through the fuel boundary layer to facilitate mixing of fuel and air in the mixing chamber.

Abstract: Methods and devices useable in turbo-engines premixing of compressed air and fuel are provided. A premixer has a mixing part configured to receive a gas flow input in a flow direction and fluid fuel injected substantially perpendicular to the flow direction. The mixing part has a rim configured to define a substantially cylindrical shape. The mixing part also has a swirler with (i) a center body located substantially in a middle of the cylindrical shape along the flow direction, and (ii) a set of vanes extending from the center body towards the rim, the vanes being configured to determine a rotation motion inside a flow that includes the received gas flow and the injected fuel when the flow passes through the mixing part, at least some of the vanes having a trailing edge with a waving profile configured to generate mixing zones inside the flow thereafter.

Abstract: A trapped vortex combustor includes a trapped vortex cavity having a first surface and a second surface. A plurality of fluidic mixers are disposed circumferentially along the first surface and the second surface of the trapped vortex cavity. At least one fluidic mixer includes a first open end receiving a first fluid stream, a coanda profile in the proximity of the first open end, a fuel plenum to discharge a fuel stream over the coanda profile, and a second open end for receiving the mixture of the first fluid stream and the fuel stream and discharging the mixture of the first fluid stream and the fuel stream in the trapped vortex cavity. The coanda profile is configured to enable attachment of the fuel stream to the coanda profile to form a boundary layer of the fuel stream and, to entrain the incoming first fluid stream to the boundary layer of the fuel stream to form a mixture of the first fluid stream and the fuel stream.

Abstract: A method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream and a second stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. The reheat combustor is cooled using the second stream of the expanded combustion gas.