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.
- International Gas Turbine Institute
The Performance of the Low NOx Aero Gas Turbine Combustor Under High Pressure
Ikezaki, T, Hosoi, J, Toh, H, Fujimori, T, Murayama, M, & Saito, T. "The Performance of the Low NOx Aero Gas Turbine Combustor Under High Pressure." Proceedings of the ASME Turbo Expo 2001: Power for Land, Sea, and Air. Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations. New Orleans, Louisiana, USA. June 4–7, 2001. V002T02A050. ASME. https://doi.org/10.1115/2001-GT-0084
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