Fuel nozzle for gas turbine engine combustor

A combustion system for a gas turbine engine, the combustion system comprising:

• a fuel nozzle comprising an inner wall and an outer wall together defining a fuel nozzle passage through which an oxidizer flows toward a combustion chamber, wherein the inner wall and the outer wall together define a contoured portion from a first radius to a second radius smaller than the first radius, and further wherein the inner wall defines a fuel injection port therethrough in fluid communication with the fuel nozzle passage, and wherein the outer wall defines a throat at the fuel nozzle passage and an exit plane at a downstream end of the outer wall adjacent to the combustion chamber, and wherein the fuel nozzle defines a forward stagnation point of the flow of oxidizer between the throat and the exit plane.