A gas turbine engine includes a first combustor having a first fuel nozzle, wherein the first fuel nozzle is configured to supply a water fuel emulsion into the first combustor. The water fuel emulsion includes a water-in-fuel (WIF) emulsion having a plurality of water droplets dispersed in a fuel, wherein the plurality of water droplets is configured to vaporize within the fuel to cause micro-explosions to atomize the fuel, and the atomized fuel is configured to combust to generate a combustion gas. The gas turbine engine further includes a turbine driven by the combustion gas from the first combustor.

A gas turbine engine includes a first combustor having a first fuel nozzle, wherein the first fuel nozzle is configured to supply a water fuel emulsion into the first combustor. The water fuel emulsion includes a water-in-fuel (WIF) emulsion having a plurality of water droplets dispersed in a fuel, wherein the plurality of water droplets is configured to vaporize within the fuel to cause micro-explosions to atomize the fuel, and the atomized fuel is configured to combust to generate a combustion gas. The gas turbine engine further includes a turbine driven by the combustion gas from the first combustor.

A power plant having a gas turbine and having a heat recovery steam generator installed downstream of the gas turbine in the direction of flow of an exhaust gas, wherein the heat recovery steam generator includes heating surfaces of a high pressure section, of an intermediate pressure section and of a low pressure section, wherein an exhaust gas recirculation line branches from the heat recovery steam generator downstream of an evaporator in the flow direction of an exhaust gas in the high pressure section and opens again into the heat recovery steam generator upstream of the heating surfaces. A blower is arranged in the exhaust gas recirculation line, with a steam feed opening into the exhaust gas recirculation line downstream of the blower in the direction of flow of a recirculated exhaust gas. A method operates a power plant of this kind.

A power plant having a gas turbine and having a heat recovery steam generator installed downstream of the gas turbine in the direction of flow of an exhaust gas, wherein the heat recovery steam generator includes heating surfaces of a high pressure section, of an intermediate pressure section and of a low pressure section, wherein an exhaust gas recirculation line branches from the heat recovery steam generator downstream of an evaporator in the flow direction of an exhaust gas in the high pressure section and opens again into the heat recovery steam generator upstream of the heating surfaces. A blower is arranged in the exhaust gas recirculation line, with a steam feed opening into the exhaust gas recirculation line downstream of the blower in the direction of flow of a recirculated exhaust gas. A method operates a power plant of this kind.

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

The present invention relates to a systems and methods for improved removal of one or more species in a process stream, such as combustion product stream formed in a power production process. The systems and methods particularly can include contacting the process stream with an advanced oxidant and with water.

The present invention relates to a systems and methods for improved removal of one or more species in a process stream, such as combustion product stream formed in a power production process. The systems and methods particularly can include contacting the process stream with an advanced oxidant and with water.

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

A power source for an aircraft having a gas turbine engine, including: an electrical connection assembly; a fuel cell assembly integrated into the gas turbine engine, electrically coupled to the connection assembly and configured to provide a first power output; and an electric machine coupled to the gas turbine engine, electrically coupled to the connection assembly and configured to provide a second power output, wherein both the first power output from the fuel cell assembly and the second power output from the electric machine are provided to the connection assembly during operating of the gas turbine engine and wherein the connection assembly is electrically coupled to an aircraft electrical load.