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 CO2separator to produce a CO2 lean airstream, reducing the operating temperature of the CO2lean airstream, and utilizing the cooled CO2lean airstream to facilitate reducing an operating temperature of air entering the gas turbine engine assembly.

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 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 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 compliant seal assembly for a rotating machine is provided. The seal assembly includes a static member, a movable member and a biasing member. The static member is rigidly fixed to the machine at its fore and aft ends. The movable portion has a first sealing surface configured to seal against a rotating member and a rear surface, which may be exposed to a fluid pressure to urge the first sealing surface toward a sealing position with the rotating member. The static and the movable members further include sealing surfaces at their fore, aft and end faces to seal against leakage of gas between the static and the movable members. The biasing member is configured to support the movable member on the static member and to urge the movable member away from the sealing position so as to reduce force on the rotating member during contact of the rotating member with the first sealing surface of the movable member.

Abstract: A method for operating a gas turbine engine including a compressor, combustor, and turbine is provided that includes channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating within, channeling the working fluid from the heat exchanger to a chiller, extracting energy from the working fluid to power the chiller, and directing airflow entering the gas turbine engine through the inlet chiller such that the temperature of the airflow is reduced prior to the airflow entering the compressor.

Abstract: A method for operating a gas turbine engine including a compressor, combustor, and turbine is provided that includes channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating within, channeling the working fluid from the heat exchanger to a chiller, extracting energy from the working fluid to power the chiller, and directing airflow entering the gas turbine engine through the inlet chiller such that the temperature of the airflow is reduced prior to the airflow entering the compressor.

Abstract: A combustor for a gas turbine engine includes a fuel delivery system that uses circumferential fuel staging. The fuel delivery system includes a plurality of fuel supply rings and a backpurge sub-system. The fuel supply rings are arranged concentrically at various radial distances to supply fuel to a combustor through a plurality of combustor manifolds and pigtails. The backpurge system uses high temperature and high pressure combustor air to purge fuel from non-flowing fuel supply rings, combustor pigtails, and combustor manifolds. Additionally, the fuel delivery system includes at least two orifices to minimize pressure decays during filling stages.

Abstract: A combustor for a gas turbine engine includes a fuel delivery system that uses circumferential fuel staging. The fuel delivery system includes a plurality of fuel supply rings and a backpurge sub-system. The fuel supply rings are arranged concentrically at various radial distances to supply fuel to a combustor through a plurality of combustor manifolds and pigtails. The backpurge system uses high temperature and high pressure combustor air to purge fuel from non-flowing fuel supply rings, combustor pigtails, and combustor manifolds. Additionally, the fuel delivery system includes at least two orifices to minimize pressure decays during filling stages.

Abstract: A method is provided for operating a gas turbine engine that includes a high pressure compressor and a water injection apparatus for injecting water into a flow of the engine upstream from the high pressure compressor. The method includes the steps of operating the engine without injecting water into the gas flow of the engine, injecting water at a first flow rate into the gas flow for power augmentation once engine full power is about reached, and injecting water into the engine at an increased second flow rate for evaporative cooling of engine components downstream from the high pressure compressor.

Abstract: A combustor for a gas turbine engine includes a fuel delivery system that uses circumferential fuel staging. The fuel delivery system includes a plurality of fuel supply rings and a backpurge sub-system. The fuel supply rings are arranged concentrically at various radial distances to supply fuel to a combustor through a plurality of combustor manifolds and pigtails. The backpurge system uses high temperature and high pressure combustor air to purge fuel from non-flowing fuel supply rings, combustor pigtails, and combustor manifolds. Additionally, the fuel delivery system includes at least two orifices to minimize pressure decays during filling stages.

Abstract: A method is provided for operating a gas turbine engine that includes a high pressure compressor and a water injection apparatus for injecting water into a flow of the engine upstream from the high pressure compressor. The method includes the steps of operating the engine without injecting water into the gas flow of the engine, injecting water at a first flow rate into the gas flow for power augmentation once engine full power is about reached, and injecting water into the engine at an increased second flow rate for evaporative cooling of engine components downstream from the high pressure compressor.