Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube. The liquid swirler includes a liquid swirler inner wall, a liquid swirler outer wall having a liquid swirler outer wall end portion at a downstream-most position and angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap has a radiused inner surface and a contoured outer surface.

Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall having a liquid swirler inner wall end portion angled radially outward from the nozzle axis, a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween.

Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage, and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall, liquid swirler outer wall having a liquid swirler outer wall end portion angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis such that it is parallel to the liquid swirler outer wall end portion, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap includes a radiused inner surface and an outer surface.

Abstract: A method of operation is provided during which a fuel-water mixture is directed within a first passage of a fuel injector to a first passage outlet of the fuel injector. The fuel-water mixture includes liquid water and gaseous fuel. The fuel-water mixture is injected into a combustion chamber through the first passage outlet. The combustion chamber is within a combustor of a turbine engine. A fuel-air mixture within the combustion chamber is ignited. The fuel-air mixture includes the gaseous fuel.

Abstract: 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.

Abstract: 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.

Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

Abstract: 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.