Abstract: A method for supplying power to a remote load includes coupling a gas turbine engine to a vessel that is not used to provide propulsion for the vessel, coupling a generator to the gas turbine engine, coupling an intercooler system downstream from a first compressor such that compressed air discharged from the first compressor is channeled therethrough, the intercooler system includes an intercooler and a first heat exchanger, channeling a first working fluid through the intercooler to facilitate reducing an operating temperature of air discharged from the intercooler to a second compressor, channeling a second working fluid flowing through the first heat exchanger to extract energy from the first working fluid to facilitate reducing an operating temperature of the first working fluid, and operating the gas turbine engine and generator to supply power to a load that is located remotely from the vessel.

Abstract: A power generation system contains a compressor stage, a pre-burner stage, a combustion stage and a turbine stage. The pre-burner stage heats a portion of flow from the compressor stage to impart a higher temperature within the flow. The heated flow is directed to the combustion stage which contains at least one pulse detonation combustor. Downstream of the combustion stage is a turbine stage. In a further embodiment of the power generation system a fuel is heated prior to the combustion within the combustion stage.

Abstract: A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Abstract: An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine.

Abstract: A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage.

Abstract: A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor.

Abstract: An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is positioned such that the inlet portion of the pulse detonation combustor is located forward of an outlet of the compressor stage with respect to the engine. The pulse detonation combustor is angled with respect to a centerline of the engine.

Abstract: A method for operating a gas turbine engine including a compressor, a combustor, and a turbine, coupled together in serial flow arrangement, and a fuel heating system including a heat exchanger and an economizer. The method includes channeling fuel through the heat exchanger, channeling a working fluid through the heat exchanger to facilitate regulating the operating temperature of the fuel and the operating temperature of the working fluid, and channeling the fuel and the working fluid into the gas turbine engine combustor to facilitate increasing a fuel efficiency of the gas turbine engine.

Abstract: Disclosed here are integrated methods and systems for producing fuel from biomass. The methods and systems pertain to gasifying a feed derived from biomass fermentate separation residue, such as corn-based distiller's grains, and producing a liquid transportation fuel component, such as aviation turbine fuel, from the gasified feed in a hydrocarbon synthesis reactor. At least a portion of the waste heat from the hydrocarbon synthesis reactor is supplied to a thermal process for liquefying, fermenting or distilling a biomass, or to a thermal process for separating or treating a biomass fermentate separation residue.

Abstract: A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the exhaust flow. The transition piece provides a non-expanding path for the exhaust flow through the transition piece, and directs the flow so as to be effective in driving the turbine when it reaches the end of the transition piece.

Abstract: Disclosed herein are systems and methods for reducing power plant CO2 emissions. In one embodiment, a method for reducing emissions in a combustion stream, comprises: combusting a gaseous stream to produce an exhaust stream comprising carbon dioxide, and separating CO2 from the exhaust stream by passing CO2 through a membrane to produce a CO2 product stream and a CO2 lean exhaust stream.

Abstract: A method for operating a power plant to facilitate reducing emissions, wherein the power plant includes a gas turbine engine assembly and a carbon dioxide (CO2) separator. The method includes increasing an operating pressure of exhaust gas discharged from the gas turbine engine assembly, separating substantially all the CO2 entrained within the gas turbine engine utilizing the CO2 separator to produce a CO2 lean airstream, reducing the operating temperature of the CO2 lean airstream, and utilizing the cooled CO2 lean airstream to facilitate reducing an operating temperature of air entering the gas turbine engine assembly.

Abstract: A method for operating a gas turbine engine includes channeling compressed airflow discharged from a first compressor through an intercooler having a cooling medium flowing therethrough, channeling a working fluid through the intercooler to facilitate increasing an operating temperature of the working fluid, and channeling the discharged working fluid to a combustor to facilitate increasing an operating efficiency of the gas turbine engine.

Abstract: A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Abstract: A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.

Abstract: A method for operating a gas turbine engine including a first compressor, a second compressor, a combustor and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor to a heat exchanger having an airstream flowing therethrough, channeling an evaporatively cooled airstream into the heat exchanger to facilitate reducing an operating temperature of the heat exchanger, and extracting energy from the compressed airflow using the heat exchanger airstream to facilitate reducing a temperature of the compressed airflow and channeling the compressed airflow from the heat exchanger to the second compressor.

Abstract: A turbine inlet air-cooling system improves turbine performance and efficiency. A dehumidifier receives process airflow and reduces a moisture content of the process airflow. An indirect evaporative cooler receives the process airflow from the dehumidifier and is driven by the process airflow from the dehumidifier such that a first portion of the process airflow is contacted directly with water and a second portion of the process airflow is cooled without any addition of moisture. A direct evaporative cooler receives the second portion of the process airflow, which is contacted directly with water to provide evaporative cooling. Subsequently, the direct evaporative cooler outputs the second portion of the process airflow to the turbine.

Abstract: A turbine inlet air-cooling system improves turbine performance and efficiency. A dehumidifier receives process airflow and reduces a moisture content of the process airflow. An indirect evaporative cooler receives the process airflow from the dehumidifier and is driven by the process airflow from the dehumidifier such that a first portion of the process airflow is contacted directly with water and a second portion of the process airflow is cooled without any addition of moisture. A direct evaporative cooler receives the second portion of the process airflow, which is contacted directly with water to provide evaporative cooling. Subsequently, the direct evaporative cooler outputs the second portion of the process airflow to the turbine.

Abstract: A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.

Abstract: A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.