[Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.

A fuel injector includes a forward end wall and an aft end wall. The fuel injector further includes side walls that extend between the forward end wall and the aft end wall. The forward end wall, the aft end wall, and the side walls collectively define an opening for passage of air. At least one fuel injection member is disposed within the opening and extends between the end walls. A fuel circuit is defined within the fuel injector. The fuel circuit includes an inlet plenum defined within the forward end wall of the fuel injector. The fuel circuit further includes a fuel passage that extends from, and is in fluid communication with, the inlet plenum. The fuel passage is defined within the at least one fuel injection member. The fuel passage has a cross-sectional area that varies along a length of the fuel injection member.

A pilot fuel nozzle assembly includes a fuel nozzle, a swirler, and a vented pilot venturi. The vented pilot venturi has an annular wall with an oxidizer flow passage therein. An expansion flow surface portion of the venturi has a larger diameter at an outlet than at a throat of the venturi. A plurality of venturi oxidizer outlet ports extend through the expansion flow surface to the oxidizer flow passage within the annular wall to provide a flow of oxidizer through the venturi wall into a mixing cavity of the venturi and at an outlet end of the venturi. The oxidizer outlet ports are circumferentially spaced about a circumference of the expansion flow surface, and may be arranged in a plurality of rows. The oxidizer outlet ports may be angled with respect to the expansion flow surface and may angled circumferentially in a co-swirl direction with the swirler.

A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.

A conduit for transport of a fluid, the conduit comprising: a wall extending around and along an axis extending parallel to a direction of bulk fluid flow. The wall having an inner surface defining an interior of a channel through which fluid flows; and a plurality of projections extending from the inner surface of the wall. The plurality of projections extend around the axis, in a plane perpendicular to the axis; and wherein the projections have a height perpendicular to the axis into the channel, and the height is arranged such that the projections modify the flow of fluid at a boundary layer of the fluid adjacent the wall. The conduit is arranged to carry a first fluid; the conduit includes an opening for introducing a second fluid into the channel such that the first and second fluid are mixed downstream of the opening and the plurality of projections are provided upstream of the opening, in a direction of fluid flow.

A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate. The positions and injection directions of fuel jet points of the primary combustion stage control fuel of the primary combustion stage to be injected into the primary-combustion-stage channel through primary-combustion-stage fuel jet orifices; and part of the fuel directly forms primary-combustion-stage direct-injection fuel spray, and the other part is hit on the pre-film plate close to an inner side of the primary-combustion-stage channel, or the two parts are respectively hit on the two layers of pre-film plates.

A nozzle for a combustor in which a fuel containing hydrogen is burned is provided. The nozzle includes a first tube disposed in a center of the nozzle and having a first diameter, a plurality of second tubes circumferentially disposed around the first tube to be spaced apart from the first tube and each having a second diameter smaller than that of the first tube, and a plurality of third tubes disposed around the first tube and each having a diameter smaller than the second diameter, wherein the first tube, the plurality of second tubes, and the plurality of third tubes are arranged in parallel with each other.

A method for operating a fuel injector of a gas turbine engine includes injecting a hydrogen-based primary fuel from a primary fuel passage of the fuel injector directly into a combustion chamber. The primary fuel passage includes a primary fuel outlet located within the combustion chamber. The method further includes injecting a second fuel, different than the hydrogen-based primary fuel, from a secondary fuel passage of the fuel injector into a hood chamber separated from the combustion chamber by a bulkhead. The secondary fuel passage includes a plurality of secondary fuel outlets located within the hood chamber.

A mixing assembly for a combustor includes: a pilot mixer including a pilot housing extending along a mixer centerline and a pilot fuel nozzle; a main mixer surrounding the pilot mixer; a fuel manifold between the pilot and main mixers; a mixer foot extending from a main housing of the main mixer; a main swirler body surrounding the main housing defining a mixing channel between the main housing and the main swirler body; and a main fuel ring in the mixing channel connected to the main housing by main fuel vanes, at least one of the main fuel ring and main fuel vanes including fuel injection ports for discharging fuel into the mixing channel, wherein the fuel injection ports are disposed non-uniformly relative to the mixer centerline, so as to produce a static pressure difference therebetween in response to mixer air flow passing around the main fuel ring.

An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.