The Performance of the Low NOx Aero Gas Turbine Combustor Under High Pressure

We have developed a new fuel staged combustor, which consists of diffusion flame pilot burners and lean premixing prevaporizing main burners and is therefore called a multiple fuel nozzle type low NOx gas turbine combustor. The goal for NOx reductions was set to 70 to 80% compared with conventional gas turbine combustors. Combustion tests for a section of the annular combustor have been performed for pressures P₃ up to 2.9Mpa and temperatures T₃ up to 823K with kerosene. As the results, even under high pressure and temperature condition, stable combustion without the problem of auto-ignition or flashback could be achieved. NOx emission index is 13 [g/kg,fuel] which is equivalent to more than 70% NOx reduction. The liner wall temperature is lower than the durability limit. The dependency of NOx emissions on pressure and temperature for this combustor are reported.