combustion section 18 and a turbine 20 as is well known in the art air compressed in the compressor 16 is mixed with fuel which is burned in the combustion section 18 and expanded in turbine 20 the air compressed in the compressor 16 and the fuel mixture expanded in the turbine 20 can both be referred to as a hot gas stream flow the turbine 20 includes rotors 22 and 24 that in response to the expansion rotate driving the compressor 16 and fan 14 the turbine 20 comprises alternating rows of rotary blades 26 and static airfoils or vanes 28 fig1 is a somewhat schematic representation for illustrative purposes only and is not a limitation of the instant invention that may be employed on gas turbines used for electrical power generation and aircraft a fuel injector or fuel nozzle is shown generally at 30 in fig1 and is shown in greater detail in fig2 the fuel nozzle 30 is positioned within the combustion section 18 and includes an engine mount end 32 and a discharge end 34 from which an air fuel mixture is discharged into a combustion chamber 36 fig1 the fuel nozzle 30 includes a fuel nozzle support portion 38 that supports a centerbody 40 fuel enters through an opening 41 air enters through.