A device for supplying fuel to a combustion chamber of a gas generator includes an injection wheel (14) for injecting fuel into the combustion chamber (18),—a fuel supply rail (20) including an internal fuel circuit (30) with a fuel outlet means (32) supplying fuel to an annular spray chamber (24) formed between the rail (28, 44, 48, 52, 56) and the injection wheel (14),—at least one dynamic annular seal (26) adapted to provide a seal between an annular face (34) of the fuel supply rail (28, 44, 48, 52, 56) and the injection wheel (14), wherein the internal fuel circuit (30) of the fuel supply rail includes an annular fuel flow part arranged radially at the dynamic annular seal (26).

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO.sub.2 gas turbine which uses supercritical CO.sub.2 for a working fluid, a casing of the suprecritical CO.sub.2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO.sub.2 gas turbine which uses supercritical CO.sub.2 for a working fluid, a casing of the suprecritical CO.sub.2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

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.

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 fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, one or more feed passages and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The one or more feed passages extend within the fuel nozzle to the gallery. The one or more feed passages are configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery.

A fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, one or more feed passages and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The one or more feed passages extend within the fuel nozzle to the gallery. The one or more feed passages are configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery.

A fuel nozzle with turning guide is included in a gas turbine. The turning guide is disposed in an air inlet of the fuel nozzle to distribute a flow of compressed air and includes at least one of a turning separator, an inner separator, and an outer separator. The fuel nozzle includes a central body having an outer wall; a shroud concentrically disposed with respect to the central body and configured to surround the central body while maintaining a space for an air passage between an inner wall of the shroud and the outer wall of the central body; a rim formed on one end of the shroud and forming an air inlet communicating with the air passage; and a turning guide including a turning separator disposed in the air inlet, to make the air flow uniform, thereby suppressing the creation of an air pocket.

A fuel nozzle with turning guide is included in a gas turbine. The turning guide is disposed in an air inlet of the fuel nozzle to distribute a flow of compressed air and includes at least one of a turning separator, an inner separator, and an outer separator. The fuel nozzle includes a central body having an outer wall; a shroud concentrically disposed with respect to the central body and configured to surround the central body while maintaining a space for an air passage between an inner wall of the shroud and the outer wall of the central body; a rim formed on one end of the shroud and forming an air inlet communicating with the air passage; and a turning guide including a turning separator disposed in the air inlet, to make the air flow uniform, thereby suppressing the creation of an air pocket.

A slinger combustor includes; a first compressed air line connected to a compressor and configured to supply compressed air; a first fuel line connected to a fuel storage and configured to supply fuel; a rotation shaft configured to rotate and inject the fuel supplied from the first fuel line; a main combustion chamber configured to receive the fuel injected from the rotation shaft and receive the compressed air from the first compressed air line; and a sub-combustion chamber configured to selectively discharge a flame generated in an inner space of the sub-combustion chamber to the main combustion chamber.