A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube.

A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube.

An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.

An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.

An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

A combustor includes a plurality of fuel nozzles installed so as to be extended in a direction of a nozzle axis and configured to inject fuel toward one side in the direction of the nozzle axis, a pipe plate having a plurality of air holes formed therein so as to be extended in the direction of the nozzle axis, in which the air hole has an inner diameter larger than a tip end portion of the fuel nozzle and the tip end portions are respectively inserted into the air holes, and a step surface formed at a position of the tip end portion closer to the other side in the direction of the nozzle axis than a tip end surface of the tip end portion so as to be expanded in a radial direction with respect to the nozzle axis from a tip end outer peripheral surface.

This invention relates to a vortex station and method for producing a vortex similar to one of a group consisting of dust-devils and waterspouts. The apparatus comprises a ground platform forming a base for the vortex station, a plurality of vanes to direct an air flow into a vortex station and about the vortex station in a substantially swirling manner, at least one wind turbine disposed near the centre of said vortex station, in a path of a concentrated air flow, wherein the movement of the air in the vortex station is such that an atmospheric buoyancy vortex is created in the centre of the vortex station, a supply of a working fluid (e.g. water) to the vortex station at or near the centre of the vortex station such that the air is of a saturated condition or an at least partially saturated condition with the working fluid (e.g. water), the working fluid (e.g. water) supplied at a sufficient quantity or amount so as to assist with maintaining buoyancy and stability of a vortex created.

This invention relates to a vortex station and method for producing a vortex similar to one of a group consisting of dust-devils and waterspouts. The apparatus comprises a ground platform forming a base for the vortex station, a plurality of vanes to direct an air flow into a vortex station and about the vortex station in a substantially swirling manner, at least one wind turbine disposed near the centre of said vortex station, in a path of a concentrated air flow, wherein the movement of the air in the vortex station is such that an atmospheric buoyancy vortex is created in the centre of the vortex station, a supply of a working fluid (e.g. water) to the vortex station at or near the centre of the vortex station such that the air is of a saturated condition or an at least partially saturated condition with the working fluid (e.g. water), the working fluid (e.g. water) supplied at a sufficient quantity or amount so as to assist with maintaining buoyancy and stability of a vortex created.

An injection system for a turbomachine combustion chamber includes a swirler and a mixing bowl. The mixing bowl includes a converging frustoconical portion and a diverging frustoconical portion. The diverging frustoconical portion is connected to the converging frustoconical portion, forming a continuous aerodynamic profile with the converging frustoconical portion. The diverging frustoconical portion is passed through by vortex holes which each includes a circumferential component around a longitudinal axis of the injection system and an axial component along the longitudinal axis of the injection system.