An engine heater system for heating a diesel engine of a vehicle. The engine heater system including a gas turbine. A heat exchanger communicatively coupled to an exhaust of the gas turbine. An electric generator including connection members to couple to a battery of the vehicle, and a shaft rotatably attached between the gas turbine and the electric generator. The heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft.

A system and method for converting hazardous waste vapors into a renewable energy source is disclosed. The system comprises a feeding system operatively coupled to a combustion system. The feeding system includes a vapor byproduct source capable of producing hydrocarbon vapors and a means for separating any liquids or particulates from the hydrocarbon vapor to create a purified vapor. The combustion system includes a compressor operable to pressurize the purified vapor to a select pressure range, a means for enriching the purified vapor with a select percentage of natural gas to form a fuel mixture, and a generator operable for converting the combined fuel mixture into electricity. Optionally, the combustion system may utilize a microturbine in combination with a fuel storage system, eductor, and a calorimeter and density meter to ensure maximum energy efficiency based on a select input range for fuel composition and pressure.

Disclosed is a fuel system for a gas turbine engine. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and a source of compressed air flow to drive the driving turbine. The source of compressed air may be the engine core, a dedicated fuel system compressor or the compressor of a cabin blower system.

A fuel injector assembly can include a manifold defining a manifold channel and a nozzle extending from the manifold. The nozzle can be configured to direct flow from the manifold channel into a combustor. The nozzle can define a fuel inlet open to the manifold channel, a fuel outlet configured to be open to a combustor, and a throat fluidly connecting the fuel inlet to the fuel outlet. The assembly can include a trim device inserted into the manifold. The trim device can be configured to adjust flow between the manifold channel and the fuel inlet to adjust flow through the throat and out of the fuel outlet.

A combustor nozzle capable of injecting fuel uniformly, and a combustor and gas turbine including the same are provided. The combustor nozzle includes a main cylinder having a fuel passage through which fuel flows, a nozzle shroud surrounding the main cylinder, and a fuel injection module disposed between the main cylinder and the nozzle shroud to inject fuel, wherein the fuel injection module includes a plurality of first struts protruding from the main cylinder and having strut injection holes to inject fuel, a first support tube coupled to outer ends of the first struts, and a plurality of second struts protruding from the first support tube and having strut injection holes to inject fuel, and each of the first and second struts includes a swirl guide inclined with respect to a longitudinal direction of the main cylinder.

A hydrogen fuel system including a fuel delivery assembly, a purge gas source, and a vent. The fuel delivery assembly is configured to receive hydrogen fuel from a hydrogen fuel source and to provide the hydrogen fuel from the hydrogen fuel source to a power generator. The purge gas source is fluidly coupled to the fuel delivery assembly and configured to provide a purge gas to the fuel delivery assembly. The vent is fluidly coupled to the fuel delivery assembly and configured to vent hydrogen fuel from the fuel delivery assembly when the purge gas is provided to the fuel delivery assembly.

An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a fuel nozzle. The fuel nozzle includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along a centerline within the fuel nozzle to the nozzle orifice. The nozzle passage has a solid polygonal cross-sectional geometry at the nozzle orifice.

An injection nozzle installed in a combustor of a gas turbine to inject fuel and compressed air into a combustion chamber is provided. The injection nozzle includes an inlet portion into which fuel and compressed air are introduced, an outlet portion disposed downstream of the inlet portion in a flow direction of fluid and configured to discharge the fuel and compressed air to the combustion chamber, and an intermediate portion disposed between the inlet portion and the outlet portion and connected obliquely to each of the inlet portion and outlet portion, wherein each of the inlet portion, the outlet portion, and the intermediate portion has a prismatic shape.

A mixer for providing a fuel-air mixer to a combustor of an engine. The mixer may include a fuel flow and an air flow entering an interior passage of the mixer. The air flow may be comprised of three separate air flows. The first air flow may be parallel to a central axis of the mixer for pulling the fuel into the interior passage. The second air flow may be inclined with respect to the central axis of the mixer and the third air flow may be tangential to the mixer body. The second air flow and the third air flow may push the fuel flow toward the interior passage and away from the boundary layer flow.