COMBUSTOR FOR GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To prevent a phenomenon of self-ignition due to stagnation of a swirl flow in a premixing/preevaporating chamber in a combustor for a gas turbine engine equipped with the premixing/preevaporating chamber. SOLUTION: A fuel nozzle 42 supplying a fuel-air mixture to a gas-phase combustion chamber 20 is equipped with a circular fuel liquid film forming passage 56 which is disposed inside in the radial direction and supplies fuel and air giving them a preliminary swirl, a circular air passage 57 which is so disposed as to surround the outer periphery of the passage 56 and supplies the air, and a nozzle tip 61 of an air blast type which joins the two passages 56 and 57 together and atomizes the fuel. The outside in the radial direction of a swirl flow of the fuel and the air supplied to a premixing/preevaporating chamber 53 from the fuel liquid film forming passage 56 is covered with a straight flow of the air supplied to the premixing/preevaporating chamber 53 from the air passage 57, thereby suppressing self-ignition in a stagnant part at the center of the swirl flow.