Emissions Reduction by Varying the Swirler Airflow Split in Advanced Gas Turbine Combustors FREE

[+] Author Affiliations
Gerald J. Micklow

Computational Fluid Dynamics Laboratory

Subir Roychoudhury

University of Florida, Gainesville, FL

H. Lee Nguyen

NASA Lewis Research Center, Cleveland, OH

Michael C. Cline

Los Alamos National Laboratory, Los Alamos, NM

Paper No. 92-GT-110, pp. V003T06A007; 8 pages
  • ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Cologne, Germany, June 1–4, 1992
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7895-8
  • Copyright © 1992 by ASME


A rich burn/quick mix/lean burn (RQL) combustor concept for reducing pollutant emissions is currently under investigation at the NASA Lewis Research Center (LeRC). A numerical study was performed to investigate the chemically reactive flow with liquid spray injection for the RQL combustor. The RQL combustor consists of an airblast atomizer fuel injector, a rich burn section, a converging connecting pipe, a quick mix zone, a diverging connecting pipe and a lean combustion zone. For computational efficiency, the combustor was split into two sub systems, i.e. the fuel nozzle/rich burn section and the quick mix/lean burn section.

The current study investigates the effect of varying the mass flow rate split between the swirler passages for an equivalence ratio of 2.0 on fuel distribution, temperature distribution, and emissions for the fuel nozzle/rich burn section of an RQL combustor. The input conditions used in the study were chosen based on tests completed at LeRC. It is seen that optimizing these parameters can substantially improve combustor performance and reduce combustor emissions. The optimal mass flow rate split for reducing NOx emissions based on the numerical study was the same as found by experiment at LeRC.

Copyright © 1992 by ASME
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