Fuel nozzle and burner section of a gas turbine engine

A fuel nozzle 51 is disclosed which comprises an inlet 55 for receiving fuel and an outlet 71 for discharging fuel. The outlet 71 intersects a longitudinal centerline CL of the nozzle 51 and produces a skewed spray pattern. Also disclosed is a fuel injector 31 having a fuel nozzle outlet 71 such that a fluid discharged from a swirler 53 produces a crescent-shaped spray pattern in the fuel. Also disclosed is a burner section 19 of a gas turbine engine comprising a combustion chamber and fuel injectors 31. At least one of the fuel injectors 31 produces a skewed flame pattern in the combustion chamber that overlaps with a flame pattern from an adjacent fuel injector 31. Also disclosed is a method of improving stability of a flame in a burner section 19 of a gas turbine engine in which at least one of the fuel injectors 31 produces a skewed flame pattern in the burner section to create a fuel non-uniformity, the flame pattern also overlapping with an adjacent flame pattern.