A rich burn/quick mix/lean burn (RQL) combustor concept for reducing pollutant emissions is currently under investigation at the NASA Lewis Research Center. The current study investigates the effect of varying the mass flow rate split between the swirler passages for an equivalance ratio of 2.0 on fuel distribution, temperature distribution, and emissions for the fuel nozzle/rich burn section of an RQL 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 NO(x) emissions based on the numerical study was the same as found by experiment.
Emissions reduction by varying the swirler airflow split in advanced gas turbine combustors
ASME, International Gas Turbine and Aeroengine Congress and Exposition ; 1992 ; Cologne, Germany
1992-06-01
Conference paper
No indication
English
Gaseous emissions of gas turbine combustors
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