A nozzle device for feeding a gaseous fuel and a liquid fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the gaseous and/or liquid fuels into the combustion chamber, a liquid fuel line for the fluidic connection between a liquid supply line system and the nozzle openings, and at least one gas fuel line for the fluidic connection between a gas supply line system and the nozzle openings. An optimized operation is achieved in that at least partly the gas fuel line is configured to be correlated with the liquid fuel line, wherein a flow cross section AiH2 of the gas fuel line is proportional to a flow cross section AiK of the liquid fuel line by a factor F, where: AiH2=F*Aik, F being 2.4-3, preferably 2.6-2.8, e.g. 2.7.

A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.

A burner for a combustor includes (a) a swirl generator enclosing a burner interior on an inlet side and including a tangential air inlet relative to a longitudinal center axis; (b) a mixing chamber enclosing the burner interior on an outlet side and defining a burner outlet fluidly connecting the burner interior with a combustion chamber; and (c) a lance arranged coaxially with the longitudinal center axis. The lance introduces fuel through a nozzle tip at or near the burner outlet into the combustion chamber. The nozzle tip includes a cartridge defining a center fuel passage; fuel swirl vanes within the center fuel passage at an outlet end of the nozzle tip; a first tube surrounding the center fuel passage and defining a first fluid passage; a second tube surrounding the first tube and defining a second fluid passage; and air swirl vanes in the second fluid passage.

A method and fuel supply system for supply of a combustion chamber with at least one combustible fluid are provided. The fuel supply system includes a combustion chamber, at least one supply circuit, and at least one purge circuit, the purge circuit coupled to the at least one supply circuit, the purge circuit including at least two isolation valves defining a cavity between, a source of relatively high temperature purge air coupled in flow communication to the cavity through one of the at least two isolation valves, a source of relatively low temperature ventilation air coupled in flow communication to the cavity, and a vent coupled in flow communication to the cavity, the at least one purge circuit configured to channel a flow of relatively low temperature ventilation air from the source relatively low temperature ventilation air through the cavity to the vent during operation of the combustion chamber.

A high excess air burner includes a housing including a generally tubular body enclosing an air chamber, a nozzle located in the air chamber and spaced radially inwardly of the generally tubular body, a fuel inlet configured to supply a variable volumetric flow rate of fuel, an air inlet configured to supply air to the air chamber, a first combustion cavity having a first inlet opening communicating with the fuel inlet for receiving the variable volumetric flow rate of fuel, a second combustion cavity having a second inlet opening communicating with the first combustion cavity for receiving the first fuel-air mixture, and a third combustion cavity having a third inlet opening communicating with the second combustion cavity for receiving the second fuel-air mixture. The burner including one or more components (e.g., nozzle, rear cover) to improve flame characteristics, such as flame stability or consistency, and/or one or more components or features to improve flame detection capability.

A fuel injection device, for a gas turbine, which enhances uniform distribution in concentration of fuel gas and water vapor in a combustion chamber with a simple structure and at low cost to effectively reduce NOx, is provided. The fuel injection device mixes fuel gas and water vapor and injects fuel gas and water vapor into a combustion chamber. The fuel injection device includes a nozzle housing having a mixing chamber, and the nozzle housing includes a first introduction passage to introduce fuel gas from an outer circumference of the nozzle housing in a circumferential direction of the mixing chamber; and a second introduction passage to introduce water vapor from the outer circumference of the nozzle housing in a circumferential direction of the mixing chamber. Fuel gas and water vapor are swirled about an axis C of the mixing chamber and mixed in the mixing chamber.

An inward-firing dual fuel combustion burner system comprising a burner casing configured to receive a gaseous mixture at a burner inlet and to provide hot combustion gas at a burner output; a combustion substrate disposed within the burner casing, the substrate having a shape comprising at least a semi-cone, having a substrate angle measured from a longitudinal axis, having a substrate porosity defined by a plurality of pores, and having a substrate inner surface and a substrate outer surface; the substrate configured to receive the fuel-air mixture at the outer surface of the substrate, the fuel-air mixture passing through the pores at a mixture flow rate from the substrate outer surface toward the substrate inner surface; one or a plurality of oil nozzles disposed within the combustion cavity defined by the substrate in fluidic communication with a source of pre-heated and pre-pressurized oil fuel, an oil nozzle configured to receive the oil fuel and disperse the oil fuel into the cavity; the burner configured to be operated using either a gaseous premix fuel air mixture or a pre-heated and pre-pressurized liquid fuel oil; the burner configured such that, during gaseous premix fuel operation, the fuel-air mixture ignites near the plurality of pores to form a respective plurality of flamelets, each flamelet corresponding to one of the pores; and the burner configured such that, during oil fuel operation, the oil mixture ignites during isenthalpic expansion.

A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.

The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.

A dual fuel burner system includes a fuel burner housing and a main fuel supply conduit within the fuel burner housing. A main fuel nozzle is positioned proximate to a downstream end of the fuel burner housing and is in fluid communication with the main fuel supply conduit. The main fuel supply conduit is configured to provide 100% of the heat input requirement of the dual fuel burner system. A secondary fuel supply conduit is within the fuel burner housing. The secondary fuel supply conduit is configured to provide 100% of the heat input requirement of the dual fuel burner system. An air circuit is in fluid communication with an outlet of the main fuel nozzle. A direct spark ignitor is positioned proximate to the outlet of the main fuel nozzle.