NASA NTRS · 19850026882
Flow modifying device
Abstract
A swirler for a gas turbine engine combustor is disclosed for simultaneously controlling combustor flow rate, swirl angle, residence time and fuel-air ratio to provide three regimes of operation. A first regime is provided in which fuel-air ratio is less than stoichiometric, NOx is produced at one level, and combustor flow rate is high. In a second regime, fuel-air ratio is nearly stoichiometric, NOx production is less than that of the first regime, and combustor flow rate is low. In a third regime, used for example at highoff, fuel-air ratio is greater than stoichiometric and the combustor flow rate is less than in either of the other regimes.
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Kelm, J. S., Vickers, E. C., Williams, J. J., Taylor, J. R.. 1985-08-13. Flow modifying device. https://ntrs.nasa.gov/citations/19850026882
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