In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.

The present disclosure provides an afterburner structure with fuel injection nozzles. In the condition of a stable inlet flow, the present disclosure forms a sweeping oscillating jet with a certain frequency at the outlet under an alternate feedback action of a feedback channel and the fluid's Coanda effect, so that the spatial uniformity of the fuel injection is improved; Therefore, without increasing the structural complexity of current afterburner of the turbo-engine and the combustion chamber of the subsonic combustion ramjet, the atomization performance and the uniformity of the oil-gas mixture in the afterburner/combustion chamber of the ramjet can be greatly improved, the combustion efficiency and combustion instability of the engine can be improved and meanwhile the length of the afterburner and the combustion chamber of the subsonic combustion ramjet is shortened.

The present disclosure provides an afterburner structure with fuel injection nozzles. In the condition of a stable inlet flow, the present disclosure forms a sweeping oscillating jet with a certain frequency at the outlet under an alternate feedback action of a feedback channel and the fluid's Coanda effect, so that the spatial uniformity of the fuel injection is improved; Therefore, without increasing the structural complexity of current afterburner of the turbo-engine and the combustion chamber of the subsonic combustion ramjet, the atomization performance and the uniformity of the oil-gas mixture in the afterburner/combustion chamber of the ramjet can be greatly improved, the combustion efficiency and combustion instability of the engine can be improved and meanwhile the length of the afterburner and the combustion chamber of the subsonic combustion ramjet is shortened.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, including a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure.

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

The subject matter of this specification can be embodied in, among other things, a fuel delivery component, including a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure.

Provided herein is a fuel injector capable of providing fuel into a jet engine operating at hypersonic speeds. Embodiments may include a system for fuel injection for an engine traveling at supersonic speeds. The system may include a fuel injection strut extending between opposing walls of an inlet to the engine, and a porous surface extending across at least a portion of the fuel injection strut. The fuel may be introduced into the inlet of the engine through the porous surface of the fuel injection strut. The porous surface of the fuel injection strut may extend along a fuel injecting portion of the fuel injection strut spaced a predefined distance from the opposing walls of the inlet. The porous portion of the fuel injection strut may include a porosity of about 100 pores per square inch or lower porosities as dictated by the specific design considerations.

A combined-cycle power plant comprises a gas turbine engine for generating exhaust gas, an electric generator driven by the gas turbine engine, a steam generator receiving the exhaust gas to heat water and generate steam, and a duct burner system configured to heat exhaust gas in the steam generator before generating the steam and that comprises a source of hydrogen fuel, a fuel distribution manifold to distribute the hydrogen fuel in a duct of the steam generator, and an igniter to initiate combustion of the hydrogen fuel in the exhaust gas. A method for heating exhaust gas in a steam generator for a combined-cycle power plant comprises directing combustion gas of a gas turbine engine into a duct, introducing hydrogen fuel into the duct, combusting the hydrogen fuel and the combustion gas to generate heated gas, and heating water in the duct with the heated gas to generate steam.

A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed. In a gas turbine combustor including a diffusion burner and a premixed burner, the premixed burner is configured with a burner liner that surrounds the diffusion burner; a burner casing that surrounds the burner liner; a plurality of vanes that separate a cylindrical space between the burner liner and the burner casing into a plurality of premixers arranged side by side in a circumferential direction; a plurality of premixed fuel nozzles that inject a premixed fuel to the premixers; at least one thermometer installed to be buried in one of the vanes, and the like, and in a case in which a detection value of the thermometer exceeds a corresponding set value, an opening of each of premixed gas control valves is reduced and an opening of a diffusion gas control valve is increased in such a manner that a sum of flow rates of fuels supplied to the diffusion burner and the premixed burner remains unchanged.