A set of stationary blades for a steam turbine is provided. At least one of the stationary blades includes a suction side and an opposite pressure side, and a plurality of ejection channels defined in the at least one stationary blade. Each of the plurality of ejection channels extends through an outer surface of the pressure side, and each of the plurality of ejection channels is coupled in flow communication to a blade inlet aperture.

A gas turbine having a compressor for compressing air, a combustor for taking in compressed air discharged from the compressor, mixing it with fuel, and burning them, and a turbine driven by combustion gas generated in the combustor, comprising: inlet guide vanes installed at a stage near an inlet of the compressor for adjusting a compressor flow rate by changing an attaching angle thereof, a steam injection mechanism for injecting steam to the combustor, a steam adjustment valve for adjusting the steam injection rate, and a steam rate control mechanism for adjusting an opening of the steam adjustment valve, a steam monitoring mechanism for monitoring the steam rate injected to the combustor, an air temperature monitoring mechanism for monitoring an atmospheric temperature, and a control unit for determining whether a restriction value of the steam injection rate using a temperature, an opening of the inlet guide vanes, and the steam injection rate as indexes is satisfied, and controlling at least one of a temperature of air flowing into the compressor, the steam injection rate, and the inlet guide vane opening.

Combined cycle gas turbine (CCGT) power plants have become common for generation of electric power due to their high efficiencies. There are various problem related with improving the efficiency of CCGT plants by optimizing the manipulated variables. The method and system for optimizing the operation of a combined cycle gas turbine has been provided. The system is configured to calculate an optimal value of manipulated variables (MV) with efficiency as one of the key performance parameters. The MVs from the existing CCGT automation system, i.e. a first set of manipulated variables and the manipulated variables from the optimization approach, i.e. a second set of manipulated variables are combined to determine an optimal set of manipulated variables. The method further checks for the anomalous behavior of the system and define the root cause of the identified anomaly and the operational state of the CCGT plant.

An engine system is provided that includes an open propulsor rotor, an engine core assembly, a bypass flowpath and a condenser. The engine core assembly is configured to drive rotation of the open propulsor rotor. The engine core assembly includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The bypass flowpath bypasses the engine core assembly. The condenser is configured to exchange heat energy between combustion products flowing within the core flowpath downstream of the combustor section and bypass air flowing within the bypass flowpath.

A power plant comprises a steam system, a first electrolyzer, a heat storage system, and a heat exchanger configured to exchange thermal energy between the steam system, the first electrolyzer and the heat storage system. A method of operating an electrolyzer in a combined cycle power plant comprises operating a steam system to convert water to steam, operating an electrolyzer in a standby mode, the electrolyzer configured to convert water and electricity to hydrogen and oxygen when the electrolyzer is in an operating mode, circulating water from the steam system through a heat exchanger, circulating a first heat transfer medium between the electrolyzer and the heat exchanger, and circulating a second heat transfer medium between the heat exchanger and a thermal storage container.

A propulsion system for an aircraft includes a hydrogen fuel system supplying hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from an exhaust gas flow and includes a plurality of spiral passages disposed within a collector. The spiraling passages generate a transverse pressure gradient to direct water out of the exhaust gas flow toward the collector.

A turbine engine assembly includes a first case structure with a first flange and a second case structure that includes a second flange. The second flange is configured for securement to the first flange at a connection interface. At least one steam conduit is in thermal communication with the connection interface and configured to receive a portion of a flow of steam to heat the connection interface. Heating the connection interface provides for control of a thermal gradient generated by a difference in temperature in temperatures on either side of the connection interface.

A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into the combustion chamber.

A turbine engine assembly includes a first case structure with a first flange and a second case structure that includes a second flange. The second flange is configured for securement to the first flange at a connection interface. At least one steam conduit is in thermal communication with the connection interface and configured to receive a portion of a flow of steam to heat the connection interface. Heating the connection interface provides for control of a thermal gradient generated by a difference in temperature in temperatures on either side of the connection interface.

A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.