A fuel system (10) for a gas turbine engine that improves efficiency by supplying fuel to a primary stage (14) and secondary stage (16) via a common fuel source (18) is disclosed. The fuel system (10) may be formed from first and second primary injector assembly stages (20, 22) and a first premix injector assembly stage (24) positioned upstream from a combustor chamber (26), whereby the first premix injector assembly stage (24) is a secondary injector system. The second primary stage (22) and the first premix stage (24) may be in fluid communication with the same fuel source (18) to eliminate duplicative components found within systems where fuel is supplied individually to the second primary stage and the first premix stage. In at least one embodiment, the second primary injector assembly stage (22) and the first premix injector assembly stage (24) may each be in communication with a fuel manifold (28) configured to supply more fuel to the second primary stage (22) than the first premix stage (24).

A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.

A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.

A system includes a metering module that receives fluid through a fluid inlet. The metering module includes a rotating component driven by the fluid, an electric machine, and a controller. The fluid is received from the fluid inlet at an inlet flow rate, and the rotating component provides the fluid to an outlet of the rotating component at an outlet pressure. The electric machine is configured to generate electrical power in response to rotation of the rotating component. The controller is powered by the electrical power generated by the electric machine, and controls a rotational speed of the rotating component to control the outlet pressure.

A multi-deck burner assembly for a conveyor-type oven can include a central manifold feeding fuel to upstream and downstream arrays of burners. Other burner assemblies can include pilot burners disposed at approximately a midway point along a longitudinal direction of the burners, thereby enabling the use of longer burners, and thus more efficient burner assembly design. Some burner assemblies can include both a centrally located manifold feeding upstream and downstream arrays and pilot burners disposed at approximately midpoints along the longitudinal lengths of both the upstream and downstream arrays.

A burner assembly for an outdoor cooker or a commercial fryer has a jet tube into which gas is injected by a nozzle on an angle oblique to the centerline of the jet tube. The nozzle is supplied gas through a manifold having gas ports. One port serves as an inlet through which gas is supplied. Another port serves as an outlet feeding gas to the nozzle. The nozzle has an exit orifice that is positioned closer to the wall of the jet tube than to the tube's centerline to minimize blockage of air into the jet tube. The oblique injection of gas and minimized air blockage help the burner assembly maintain a high-temperature blue flame.

A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force.

Methods and systems for a fire device, comprising a common fuel line coupled to a fuel source via a first pressure regulator, wherein the first pressure regulator is configured to provide gaseous fuel from the fuel source to the common fuel line at a first pressure. A first fire display device is coupled to the common fuel line via a second pressure regulator, wherein the second pressure regulator is positioned downstream of the first pressure regulator and provides the gaseous fuel to the first fire display device at a second pressure that is lower than the first pressure.

A burner (1) for producing a flame for a heat generation system, comprising a fuel supply line (3) and at least one a comburent intake system operatively connected to the combustion head (2) for supplying a flow rate of fuel and a flow rate of comburent, respectively, to the burner (1). The burner (1) comprises a turbogas unit having an auxiliary combustion chamber (6) in which combustion takes place and for the generation and conveying, downstream, of a flow of flue gases; and a turbine (7) activated by the flue gases produced by the auxiliary combustion chamber (6). In particular, the turbine (7) is operatively active to contribute at least partially to the movement of the fuel in said comburent supply system (4).

The fuel preheater includes a first mixer provided in a fuel supply line connected to a combustion facility that combusts fuel including ammonia, the fuel supply line supplying ammonia to the first mixer, the first mixer being connected to an oxidizer supply line that supplies an oxidizer and mixing the ammonia flowing in the fuel supply line with the oxidizer from the oxidizer supply line to produce a mixed gas, and a reactor provided downstream of the first mixer in the fuel supply line, the reactor including a catalyst that promotes a reaction of the ammonia and that causes an exothermic reaction, the catalyst causing the exothermic reaction with at least a part of the ammonia in the mixed gas that is supplied from the first mixer and heating the mixed gas.