Patent ID: 8281595

Claim:
A fuel nozzle assembly for a combustor of a gas turbine comprising: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front is proximate to a combustion section of the combustor; an outer casing around the inner tube and the outer casing includes a weakened region, wherein an air passage is defined between the outer casing and the inner tube; an expandable fuel conduit arranged in the air passage and radially outward of the inner tube, an expandable fuel conduit having an outlet which is both proximate to the front of the nozzle body and adjacent the weakened region, wherein fuel flows through an expandable fuel conduit only after a flashback condition occurs in the combustor and opens the weakened region, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein an expandable fuel conduit has an inlet open to the premix fuel passage and the port is radially outward of the outer casing.