A turbine engine comprising: a compressor section, a combustion section, and a turbine section in serial flow arrangement; and a combustor, provided within the combustion section, the combustor comprising: a dome wall and a combustor liner collectively forming a combustion chamber and a plurality of fuel injectors (240, 340) extending through a respective portion of the dome wall, the fuel injectors (240, 340) provided in an annular arrangement, the fuel injectors comprising: a fuel channel (220, 320, 236, 336), wherein the fuel channel defines a centerline axis, terminates at a distal end, and is fluidly coupled to a fuel (F, F1, F2); a wall (250, 350) provided within the fuel channel, the wall including a first set of fuel orifices (222, 322) extending therethrough and fluidly coupling the fuel channel (220, 320, 236, 336) to the combustion chamber; and a flow restrictor (224, 324) located within the fuel channel (220, 320, 236, 336), upstream of and spaced from the first set of fuel orifices (222, 322), and having a second set of fuel orifices (226, 326) fluidly coupled to the first set of fuel orifices (222, 322); wherein a diameter of the fuel channel (220, 320, 236, 336) at the wall (250, 350) is the same as the diameter of the fuel channel at the flow restrictor (224, 324)wherein the flow restrictor (224, 324) includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis (230, 330) and intersecting the first portion to define a first protrusion (232, 332). a compressor section, a combustion section, and a turbine section in serial flow arrangement; and a combustor, provided within the combustion section, the combustor comprising: a dome wall and a combustor liner collectively forming a combustion chamber and a plurality of fuel injectors (240, 340) extending through a respective portion of the dome wall, the fuel injectors (240, 340) provided in an annular arrangement, the fuel injectors comprising: a fuel channel (220, 320, 236, 336), wherein the fuel channel defines a centerline axis, terminates at a distal end, and is fluidly coupled to a fuel (F, F1, F2); a wall (250, 350) provided within the fuel channel, the wall including a first set of fuel orifices (222, 322) extending therethrough and fluidly coupling the fuel channel (220, 320, 236, 336) to the combustion chamber; and a flow restrictor (224, 324) located within the fuel channel (220, 320, 236, 336), upstream of and spaced from the first set of fuel orifices (222, 322), and having a second set of fuel orifices (226, 326) fluidly coupled to the first set of fuel orifices (222, 322); wherein a diameter of the fuel channel (220, 320, 236, 336) at the wall (250, 350) is the same as the diameter of the fuel channel at the flow restrictor (224, 324)wherein the flow restrictor (224, 324) includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis (230, 330) and intersecting the first portion to define a first protrusion (232, 332). a fuel channel (220, 320, 236, 336), wherein the fuel channel defines a centerline axis, terminates at a distal end, and is fluidly coupled to a fuel (F, F1, F2); a wall (250, 350) provided within the fuel channel, the wall including a first set of fuel orifices (222, 322) extending therethrough and fluidly coupling the fuel channel (220, 320, 236, 336) to the combustion chamber; and a flow restrictor (224, 324) located within the fuel channel (220, 320, 236, 336), upstream of and spaced from the first set of fuel orifices (222, 322), and having a second set of fuel orifices (226, 326) fluidly coupled to the first set of fuel orifices (222, 322); wherein a diameter of the fuel channel (220, 320, 236, 336) at the wall (250, 350) is the same as the diameter of the fuel channel at the flow restrictor (224, 324)wherein the flow restrictor (224, 324) includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis (230, 330) and intersecting the first portion to define a first protrusion (232, 332).