A system and method are provided for a compressed air energy storage (CAES) system. The system and method may include compressing a process gas with a compressor train to produce a compressed process gas. The compressed process gas may be directed to a compressed gas storage unit and stored therein. The compressed process gas from the compressed gas storage unit may be released to a heat recovery unit via a feed line. The heat recovery unit may heat the compressed process gas and direct the heated compressed process gas to an expansion assembly to generate a power output. Feed water from a feed water source may be heated in the heat recovery unit to produce steam for injection into a combustion turbine assembly. The combustion turbine assembly may heat the heat recovery unit via an exhaust line.

A method of power production using a high pressure/low pressure ratio Brayton Power cycle with predominantly N.sub.2 mixed with CO.sub.2 and H.sub.2O combustion products as the working fluid is provided. The high pressure can be in the range 80 bar to 500 bar. The pressure ratio can be in the range 1.5 to 10. The natural gas fuel can be burned in a first high pressure combustor with a near stoichiometric quantity of pressurized preheated air and the net combustion gas can be mixed with a heated high pressure recycle N.sub.2+CO.sub.2+H.sub.2O stream which moderates the mixed gas temperature to the value required for the maximum inlet temperature to a first power turbine producing shaft power.

A system and method are provided for a compressed air energy storage (CAES) system. The system and method may include compressing a process gas with a compressor train to produce a compressed process gas. The compressed process gas may be directed to a compressed gas storage unit and stored therein. The compressed process gas from the compressed gas storage unit may be released to a heat recovery unit via a feed line. The heat recovery unit may heat the compressed process gas and direct the heated compressed process gas to an expansion assembly to generate a power output. Feed water from a feed water source may be heated in the heat recovery unit to produce steam for injection into a combustion turbine assembly. The combustion turbine assembly may heat the heat recovery unit via an exhaust line.

A thermal power plant for recovering water from exhaust gas comprising: a gas turbine; a heat recovery steam generator for generating steam by supplying exhaust combustion gas exhausted from the gas turbine as heat source; a water recovery system installed on the downstream side of the heat recovery steam generator for condensing and recovering water in the exhaust combustion gas through direct gas/liquid contact between the exhaust combustion gas coming down from the heat recovery steam generator and water; a recovered water system for supplying a part of the water recovered by the water recovery system, thereby allowing the water to be circulating as circulating water; a feed water system for supplying the heat recovery steam generator with other part of the water recovered by the water recovery system as feed water; a first pH adjusting system installed in the recovered water system to adjust the circulating water flowing through the recovered water system to a first pH value (hydrogen ion concentration index); a second pH adjusting system installed on the feed water system to adjust the feed water flowing through the feed water system to a second pH value (hydrogen ion concentration index); and a control system for controlling the volumes of the pH adjusters supplied from the first pH adjusting system and the second pH adjusting system.

A propulsion system for an aircraft includes at least two steam generation assemblies that each include a condenser where water is extracted from the gas flow and an evaporator where the extracted water is heated to generate a portion of a total steam flow for injection into the core flow path. A monitoring system is configured to gather information indicative of operation of each of the at least two steam generation assemblies. A control system is configured to independently adjust operation of each of the at least two steam generation assemblies.

A propulsion system for an aircraft includes at least two steam generation assemblies that each include a condenser where water is extracted from the gas flow and an evaporator where the extracted water is heated to generate a portion of a total steam flow for injection into the core flow path. A monitoring system is configured to gather information indicative of operation of each of the at least two steam generation assemblies. A control system is configured to independently adjust operation of each of the at least two steam generation assemblies.

The disclosed concept relates to a novel modified and simplified Rankine steam-turbine cycle without rejection of heat in the cycle, which is driven by a thermocompressor (ejector) operating in the wet-vapor region, to the end of achieving of the maximum possible (100%) thermal efficiency of the thus modified Rankine cycle. Wet-vapor mixture circulating within the thermocompressor is being separated in a cylindrical separation tank, so that the saturated water is pumped to a water heater where it receives the cycle heat input, while the saturated vapor is expanded in a backpressure steam turbine producing useful mechanical work and is then recirculated back to the thermocompressor, where it is being re-pressurized by the primary fluid (pumped and heated saturated water). The concept can be applied to steam-turbine-cycle power-plants fueled by: coal or solid/liquid/waste fuel, nuclear fuel (using boiling water reactors, pressurized water reactors, pressurized heavy-water reactors, gas-cooled reactors, molten salt reactors or liquid-metal-cooled fast reactors) or renewable energy sources (Solar energy, biomass, geothermal), The concept can also be used in the form of the bottoming steam-turbine-cycle part of a combined gas-turbine/steam-turbine cycle power plant.

The present disclosure relates to a gas turbine plant which decomposes ammonia and supplies it as fuel to a combustor of the gas turbine. The gas turbine plant supplies sufficient heat to the ammonia in order to thermally decompose the ammonia effectively, and separates the residual ammonia present in the decomposition gas and supplies it to a combustor of the gas turbine.

A modified combined-cycle gas power system includes a mixed fuel preheat coil, a heat recovery steam generator (HRSG), and a parallel connection coupling a gas turbine to the mixed fuel preheat coil and the HRSG for receiving gas turbine exhaust (GTE). In some cases, the system further includes a GTE flow controller coupled to the parallel connection to control a ratio of the GTE received by the mixed fuel preheat coil and the HRSG. In some cases, the parallel connection from the gas turbine to the mixed fuel preheat coil and the HRSG is a single exhaust duct having an internal separator baffle. In some cases, the parallel connection from the gas turbine to the mixed fuel preheat coil and the HRSG is dual exhaust ducts. In some cases, the mixed fuel preheat coil does not include a burner or catalyst for generating reformed fuel.

A turbine engine assembly includes a core engine that generates an exhaust gas flow, a condenser where water is extracted from the exhaust gas flow, an evaporator where heat is input into the water that is extracted by the condenser to generate a first steam flow, a first steam turbine where the first steam flow is expanded and cooled to generate a first cooled flow, a bypass passage that defines a path for the first steam flow around the first steam turbine, and a superheater where at least one of the first steam flow and the first cooled flow is reheated to generate a second steam flow.