A fuel supply nozzle unit includes a fuel supply nozzle, a rear end and an end plate. The fuel supply nozzle includes a front end that has a plurality of fuel supply holes. The rear end extends from the front end and is formed with a threaded portion on its outer surface. The end plate is connected to the rear end and is formed with a plurality of threaded holes.

A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

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 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 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 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.

One object of the present invention is to provide a burner which makes it possible to prevent blockage and damage of the nozzle by the molten metal and the slag, and the present invention provides a burner including a combustion supporting gas supply passage which is configured to supply a combustion supporting gas toward a combustion supporting gas outlet provided at the center of the tip end side; a fuel supply passage which is configured to supply a fuel toward a fuel ejection outlet provided around the combustion supporting gas outlet; and a protective nozzle provided from a position surrounding a periphery of the fuel ejection outlet so as to project forward beyond the tip end surface at which the combustion supporting gas ejection outlet and the fuel ejection outlet are provided; wherein the combustion supporting gas supply passage includes a Laval nozzle, and a diameter-enlarged nozzle of which a diameter gradually increases from the tip end of the Laval nozzle toward the combustion supporting gas ejection outlet, and the protective nozzle has a shape which is gradually reduced in diameter forward from the tip end surface.

One object of the present invention is to provide a burner which makes it possible to prevent blockage and damage of the nozzle by the molten metal and the slag, and the present invention provides a burner including a combustion supporting gas supply passage which is configured to supply a combustion supporting gas toward a combustion supporting gas outlet provided at the center of the tip end side; a fuel supply passage which is configured to supply a fuel toward a fuel ejection outlet provided around the combustion supporting gas outlet; and a protective nozzle provided from a position surrounding a periphery of the fuel ejection outlet so as to project forward beyond the tip end surface at which the combustion supporting gas ejection outlet and the fuel ejection outlet are provided; wherein the combustion supporting gas supply passage includes a Laval nozzle, and a diameter-enlarged nozzle of which a diameter gradually increases from the tip end of the Laval nozzle toward the combustion supporting gas ejection outlet, and the protective nozzle has a shape which is gradually reduced in diameter forward from the tip end surface.

A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.