A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

Described herein are catalytic heating systems, comprising catalytic reactors and dual-mode fuel evaporators, and methods of operating such systems. A dual-mode fuel evaporator is thermally coupled to a catalytic reactor and comprises an electric heater used for preheating the evaporator to at least a fuel-flow threshold temperature. Upon reaching this threshold, the liquid fuel, such as ethanol or methanol, is flown into the evaporator and evaporates therein, forming vaporized fuel. The vaporized fuel is mixed with oxidant, and the mixture is flown into the catalytic reactor where the vaporized fuel undergoes catalytic exothermic oxidation. At least some heat, generated in the catalytic reactor, is transferred to the evaporator and used for the evaporation of additional fuel. When the evaporator reaches or exceeds its operating threshold, the electric heater can be turned off and all heat is supplied to the evaporator from the catalytic reactor.

Described herein are catalytic heating systems, comprising catalytic reactors and dual-mode fuel evaporators, and methods of operating such systems. A dual-mode fuel evaporator is thermally coupled to a catalytic reactor and comprises an electric heater used for preheating the evaporator to at least a fuel-flow threshold temperature. Upon reaching this threshold, the liquid fuel, such as ethanol or methanol, is flown into the evaporator and evaporates therein, forming vaporized fuel. The vaporized fuel is mixed with oxidant, and the mixture is flown into the catalytic reactor where the vaporized fuel undergoes catalytic exothermic oxidation. At least some heat, generated in the catalytic reactor, is transferred to the evaporator and used for the evaporation of additional fuel. When the evaporator reaches or exceeds its operating threshold, the electric heater can be turned off and all heat is supplied to the evaporator from the catalytic reactor.

A system comprises a gas turbine engine including a compressor, combustor, gas turbine, the combustor including a plurality of late lean fuel injectors; and wash system configured to be attached to and in fluid communication with the a plurality of late lean fuel injectors of the combustor. The wash system includes a water source supplying water; a first fluid source supplying a first fluid; a mixing chamber in communication with the water source and first fluid source; a water pump to pump water to the mixing chamber; a first fluid pump to pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and at least one of the plurality of late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at late lean fuel injectors. The wash system is operated with the gas turbine engine off-line.

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

Liquid fuel supply system (12) for a combustion system (14), in particular a gas turbine, including at least one storage tank (16) for liquid fuel supplying at least one injector (34) connected to a combustion chamber (32) of the combustion system (14), said liquid fuel supply system (12) including a first piping section (18) disposed downstream of the tank (16) and a second piping section (20) disposed downstream of the first piping section (18) and upstream of fuel nozzle (34) in each combustion chamber (32), said first piping section (18) including at least one pressurizing means (22), and at least one injecting point or entering (24) for a water-soluble product, and the second piping section (20) including a mixing and distribution flow device (26) configured to create an emulsion and distributing the emulsion flow rate to at least one piping (28) connected to said nozzle (34).

Liquid fuel supply system (12) for a combustion system (14), in particular a gas turbine, including at least one storage tank (16) for liquid fuel supplying at least one injector (34) connected to a combustion chamber (32) of the combustion system (14), said liquid fuel supply system (12) including a first piping section (18) disposed downstream of the tank (16) and a second piping section (20) disposed downstream of the first piping section (18) and upstream of fuel nozzle (34) in each combustion chamber (32), said first piping section (18) including at least one pressurizing means (22), and at least one injecting point or entering (24) for a water-soluble product, and the second piping section (20) including a mixing and distribution flow device (26) configured to create an emulsion and distributing the emulsion flow rate to at least one piping (28) connected to said nozzle (34).

A method and system for cleaning a fuel nozzle during engine operation is provided. Operations include operating the compressor section to provide the flow of oxidizer at a first oxidizer flow condition to the combustion chamber, wherein the first oxidizer flow condition comprises an environmental parameter; operating the fuel system at a first fuel flow condition to produce a fuel-oxidizer ratio at the combustion chamber; comparing the environmental parameter to a first environmental parameter threshold; and transitioning the fuel system to a second fuel flow condition corresponding to a cleaning condition at the fuel nozzle if the environmental parameter is equal to or greater than the first environmental threshold.

A fuel injector includes an outer body and an inner body. The outer body extends about an axis and has a radially inner surface and a retention groove defined in the inner surface of the outer body. The inner body is positioned within the outer body has an outer surface and a retention tab. The retention tab retains the inner body relative to the outer body by engagement of the retention tab within the retention groove. A is axially offset from the retention tab and fixes the inner body within the outer body.