Fuel nozzle and swirler
An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.
1 . A turbine engine comprising:
a compressor section, combustor section, and turbine section in serial flow arrangement about a rotational axis, and having a fuel nozzle assembly, the fuel nozzle assembly comprising:
a fuel nozzle terminating at a nozzle tip, defining a fuel passage, and defining a longitudinal axis, the fuel passage supplying fuel unmixed with air to the nozzle tip;
a nozzle cap positioned within the fuel nozzle and spaced from the nozzle tip, the nozzle cap having an elliptical shape defining a major axis and a minor axis, a diameter of the nozzle cap along the major axis being greater than a diameter of the nozzle cap along the minor axis;
a set of fuel openings provided in the nozzle cap with a greater amount of the set of fuel openings distributed closer to the major axis than the minor axis; and
a swirler circumscribing the fuel nozzle assembly.
2 . The turbine engine of claim 1 , wherein the set of fuel openings collectively define a total area, wherein the greater amount of the set of fuel openings distributed closer to the major axis is defined by a greater amount of the total area distributed closer to the major axis than the minor axis.
3 . The turbine engine of claim 1 , wherein the greater amount of the set of fuel openings distributed closer to the major axis is defined by a greater number of the set of fuel openings arranged along the major axis than the minor axis.
4 . The turbine engine of claim 1 , wherein the set of fuel openings further comprises a central opening intersected by both the major axis and the minor axis.
5 . The turbine engine of claim 1 , wherein at least one fuel opening of the set of fuel openings is an elliptical opening.
6 . The turbine engine of claim 5 , wherein at least one fuel opening of the set of fuel openings is a circular opening.
7 . The turbine engine of claim 5 , wherein the elliptical opening includes an opening major axis that is aligned with the major axis for the nozzle cap.
8 . The turbine engine of claim 5 , wherein the elliptical opening includes an opening major axis that is arranged perpendicular to the major axis for the nozzle cap.
9 . The turbine engine of claim 5 , wherein the elliptical opening includes an opening major axis that is arranged parallel to the major axis for the nozzle cap.
10 . The turbine engine of claim 1 , further comprising an outer wall provided between the fuel nozzle and the swirler, and wherein a cross-sectional thickness for the outer wall varies between the major axis and the minor axis.
11 . The turbine engine of claim 10 , wherein the cross-sectional thickness for the outer wall is smallest at the major axis and greatest at the minor axis.
12 . The turbine engine of claim 1 , wherein the swirler defines a swirler passage arranged about the fuel nozzle, and wherein the swirler passage includes an elliptical cross-sectional shape.
13 . The turbine engine of claim 12 , wherein a cross-sectional area for the swirler passage is greater at the minor axis and smaller at the major axis.
14 . The turbine engine of claim 1 , wherein the major axis is arranged at an offset angle relative to a tangential axis defined tangent to a circumferential direction defined circumferentially about the rotational axis.
15 . A fuel nozzle assembly comprising:
a fuel nozzle terminating at a nozzle tip, defining a fuel passage, and defining a longitudinal axis, the fuel passage supplying fuel unmixed with air to the nozzle tip;
a nozzle cap positioned within the fuel nozzle and spaced from the nozzle tip, the nozzle cap having an elliptical shape, an oval shape, or a stadium shape, the nozzle cap defining a major axis and a minor axis, a diameter of the nozzle cap along the major axis being greater than a diameter of the nozzle cap along the minor axis;
a set of fuel openings provided in the nozzle cap collectively defining a total area, wherein the set of fuel openings are arranged in the nozzle cap such that a greater amount of the total area is distributed closer to the major axis than the minor axis; and
a swirler circumscribing the fuel nozzle assembly.
16 . The fuel nozzle assembly of claim 15 , wherein a greater amount of the set of fuel openings distributed closer to the major axis is defined by a greater number of the set of fuel openings arranged along the major axis than the minor axis.
17 . The fuel nozzle assembly of claim 15 , wherein the swirler includes an elliptical cross-sectional shape.
18 . The fuel nozzle assembly of claim 17 , wherein a swirler passage is defined between the swirler and the fuel nozzle, and wherein the swirler passage includes a constant cross-sectional distance between the swirler and the fuel nozzle.
19 . A fuel nozzle assembly comprising:
a fuel nozzle terminating at a nozzle tip, defining a fuel passage, and defining a longitudinal axis;
a nozzle cap positioned within the fuel nozzle and spaced from the nozzle tip, the nozzle cap having an elliptical shape, an oval shape, or a stadium shape, the nozzle cap defining a major axis and a minor axis;
a set of fuel openings provided in the nozzle cap collectively defining a total area, wherein the set of fuel openings are arranged in the nozzle cap such that a greater amount of the total area is distributed closer to the major axis than the minor axis; and
a swirler circumscribing the fuel nozzle assembly, wherein a swirler passage is defined between the swirler and the fuel nozzle, and wherein the swirler passage includes a constant cross-sectional distance between the swirler and the fuel nozzle;
wherein the set of openings is arranged into a central opening, a radially inner set of openings, and a radially outer set of openings.
20 . The fuel nozzle assembly of claim 19 , wherein at least one of the radially inner set of openings or the radially outer set of openings are in elliptical arrangement.
21 . A turbine engine comprising:
a compressor section, combustor section, and turbine section in serial flow arrangement about a rotational axis, and having a fuel nozzle assembly, the fuel nozzle assembly comprising:
a fuel nozzle terminating at a nozzle tip, defining a fuel passage, and defining a longitudinal axis;
a nozzle cap positioned within the fuel nozzle and spaced from the nozzle tip, the nozzle cap having an elliptical shape defining a major axis and a minor axis, a diameter of the nozzle cap along the major axis being greater than a diameter of the nozzle cap along the minor axis;
a set of fuel openings provided in the nozzle cap with a greater amount of the set of fuel openings distributed closer to the major axis than the minor axis; and
a swirler circumscribing the fuel nozzle assembly;
wherein the set of openings is arranged into a central opening, a radially inner set of openings, and a radially outer set of openings.
22 . The fuel nozzle assembly of claim 21 , wherein at least one of the radially inner set of openings or the radially outer set of openings are in elliptical arrangement.