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 extending through a respective portion of the dome wall, the fuel injectors provided in an annular arrangement, the fuel injectors comprising: a fuel channel , 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 provided within the fuel channel, the wall including a first set of fuel orifices extending therethrough and fluidly coupling the fuel channel to the combustion chamber ; and a flow restrictor located within the fuel channel , upstream of and spaced from the first set of fuel orifices , and having a second set of fuel orifices fluidly coupled to the first set of fuel orifices ; wherein a diameter of the fuel channel at the wall is the same as the diameter of the fuel channel at the flow restrictor wherein the flow restrictor includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis and intersecting the first portion to define a first protrusion . 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 extending through a respective portion of the dome wall, the fuel injectors provided in an annular arrangement, the fuel injectors comprising: a fuel channel , 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 provided within the fuel channel, the wall including a first set of fuel orifices extending therethrough and fluidly coupling the fuel channel to the combustion chamber ; and a flow restrictor located within the fuel channel , upstream of and spaced from the first set of fuel orifices , and having a second set of fuel orifices fluidly coupled to the first set of fuel orifices ; wherein a diameter of the fuel channel at the wall is the same as the diameter of the fuel channel at the flow restrictor wherein the flow restrictor includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis and intersecting the first portion to define a first protrusion . a fuel channel , 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 provided within the fuel channel, the wall including a first set of fuel orifices extending therethrough and fluidly coupling the fuel channel to the combustion chamber ; and a flow restrictor located within the fuel channel , upstream of and spaced from the first set of fuel orifices , and having a second set of fuel orifices fluidly coupled to the first set of fuel orifices ; wherein a diameter of the fuel channel at the wall is the same as the diameter of the fuel channel at the flow restrictor wherein the flow restrictor includes a first portion and a second portion, and wherein the second portion extends axially outwardly from a plane normal to the centerline axis and intersecting the first portion to define a first protrusion . <EOS>