| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of reducing the pressure loss of the gas turbine combustor without increasing NOx emission.SOLUTION: In a gas turbine combustor including: a burner constituted by a plurality of fuel nozzles injecting fuel, and a plurality of air holes formed in an air hole plate located downstream of the fuel nozzles and arranged to be paired with the respective fuel nozzles; and a combustion chamber mixing the fuel injected from the fuel nozzles constituting this burner with air injected from the air holes, and combusting gas mixture, each of the fuel nozzles constituting the burner each is formed into a shape having a protrusion configured so that part of an outer edge of a cross-section of the fuel nozzle protrudes outward, each fuel nozzle is arranged so that this protrusion faces toward a center of the gas turbine combustor, and the protrusion of each fuel nozzle is located downstream of a flow of the combustion air flowing around the fuel nozzle.</p> |
