A combustor nozzle capable of injecting fuel uniformly, a combustor including the combustor nozzle, and a gas turbine including the combustor are provided. The combustor nozzle includes a premix passage in which air and fuel are mixed, wherein the premix passage includes a plurality of pegs configured to inject fuel and guide an air flow and a plurality of mixing bars configured to mix air and fuel injected from the plurality of pegs, the mixing bar having a twisted structure.

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, which includes a primary combustion zone with a primary combustion zone depth and a secondary combustion zone. A ratio of the primary combustion zone depth to the lean burn fuel injector head tip diameter is less than 2.4.

A combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated.

A fuel injector for an aircraft gas turbine engine includes a housing stem, a fuel nozzle coupled to the housing stem, and a fuel conduit extending through the housing stem and into the fuel nozzle where the fuel conduit bends to extend in a longitudinal downstream direction within the fuel nozzle. The fuel conduit is configured to transport bulk fuel flow further along the nozzle before being split downstream in the fuel circuit for final spray distribution, thereby promoting lower fuel temperatures. The fuel nozzle may minimize metal-to-metal contact between an external wall of the nozzle in thermal communication with ambient environment and an internal portion of the nozzle in thermal communication with the fuel circuit to minimize heat pick-up in the fuel. The fuel conduit may include a coiled section within a cavity of the fuel nozzle for compensating for thermal growth mismatches of the fuel injector.

A fuel injection device (70) includes a nozzle body (72) and a stem portion (110) connected to the rear end of the nozzle body at an angle. The stem portion is provided at a free end thereof with an annular wall member (128) defining a recess that receives the rear end of the nozzle body. The stem portion is covered by a heat insulating sleeve (122), and a part of the heat insulating sleeve adjacent to the free end of the stem portion is provided with a cutout (122B) exposing a part of the outer circumferential surface (128A) of the annular wall member. The exposed part of the annular wall member is provided with a heat insulating groove (130) opening at an end surface (128B) of the annular wall member facing the nozzle body.

A nozzle for a combustion chamber of an engine for providing a fuel-air mixture at a nozzle exit opening of the nozzle includes a nozzle main body including the nozzle exit opening and extends along a nozzle longitudinal axis. The nozzle main body has a first air guiding channel, a fuel guiding channel and a further, radially outwardly second air guiding channel. One end of the fuel guiding channel is positioned in front of the end of the second air guiding channel. A tapering channel portion with a shell surface inclined with respect to a nozzle longitudinal axis in the axial direction and connects to a radially outer shell surface of the fuel guiding channel is formed between the end of the fuel guiding channel and the end of the second air guiding channel at the nozzle.

In a combustor, and in a gas turbine including the same, a path in which compressed air is mixed with fuel may be increased in each of a plurality of main nozzles. The combustor includes a nozzle casing axially extending in parallel with an extension line (PL); and a plurality of main nozzles to mix and inject compressed air and fuel, the plurality of main nozzles arranged inside the nozzle casing along an imaginary annular line, at least one main nozzle having a center axis inclined at a predetermined angle with respect to the extension line. A central nozzle surrounded by the main nozzles may be disposed in the nozzle casing so as to be parallel to the extension line. Thus, the at least one main nozzle has a path in which the fuel and the compressed air flow that is longer than in the central nozzle.

A spacer for a fluid nozzle can include a body configured to fit within a sheath of the fluid nozzle such that a fluid tube positioned within the sheath is held bent over its longitudinal dimension by the body thereby altering a natural frequency of the fuel tube compared to if the fuel tube were not held bent.

A mixing assembly includes a pilot mixer and a main mixer. The main mixer includes a main housing, a fuel manifold positioned between a pilot housing and the main housing, a mixer foot extending outward from a forward end of the main housing, and a main swirler body including a plurality of vanes. The main swirler body surrounds the main housing and defines an annular mixing channel between the main housing and the main swirler body, and being coupled to the mixer foot. An annular main fuel ring extends axially aft from the mixer foot into the annular mixing channel. The mixer foot extends farther from the main housing than the main fuel ring. At least one of the mixer foot or the main fuel ring includes a plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel.