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

[+] Author and Article Information
G. J. Micklow

Computational Fluid Dynamics Laboratory, Mechanical Engineering Department, University of Florida, Gainesville, FL 32601

S. Roychoudhury

University of Florida, Gainesville, FL 32601

H. L. Nguyen

Combustion Technology, NASA Lewis Research Center, Cleveland, OH 44155

M. C. Cline

Los Alamos National Laboratory, Los Alamos, NM 88888

J. Eng. Gas Turbines Power 115(3), 563-569 (Jul 01, 1993) (7 pages) doi:10.1115/1.2906744 History: Received February 06, 1992; Online April 24, 2008


A staged combustor concept for reducing pollutant emissions is currently under investigation. A numerical study was performed to investigate the chemically reactive flow with liquid spray injection for staged combustion. The staged 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 subsystems, 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 a staged combustor. 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.

Copyright © 1993 by The American Society of Mechanical Engineers
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