Abstract
An experimental program was conducted to evaluate low NOx combustor concepts applicable to natural-gas-burning aeroderivative gas turbine engines operating at a nominal pressure ratio of 20:1. Gas sampling measurements at the exit of the primary zone of high-shear and lean premixed burners were acquired under elevated entrance pressure and temperature conditions over a range of primary zone equivalence ratios. Piloting systems were incorporated in most of the burner designs to achieve satisfactory burner operabilily. Both swirl stabilized and perforated-plate (grid) stabilized burners were found to produce NOx levels lower than the current engine goal of 25 ppm (15%O2).
Cite
CITATION STYLE
McVey, J. B., Padget, F. C., Rosfjord, T. J., Hu, A. S., Peracchio, A. A., Schlein, B., & Tegel, D. R. (1992). Evaluation of low NOX combustor concepts for aeroderivative gas turbine engines. In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, GT 1992 (Vol. 3). American Society of Mechanical Engineers. https://doi.org/10.1115/92-GT-133
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