To support the development of a rich quench lean pilot zone for a staged aeroengine combustor, two rectangular rich quench lean (RQL) combustor sectors have been investigated under atmospheric conditions. Two advanced cooling mixing concepts, effusion and impingement cooling, with one and two rows of secondary air inlet holes in the mixing zone, have been measured using intrusive and noninstrusive measurement techniques. The results elucidate the interrelations between the cooling concepts and the respective mixing and emissions performances. The measurements were accompanied by numerical calculations supporting the interpretations of the measured data. Drawbacks were observed for the near stoichiometric conditions of the effusion cooling concept near the wall, however, the quench zone design with two rows of staggered holes performs well. On the contrary, the impingement cooling system shows good results for the homogeneity of the primary zone, but since less quench air is available with impingement cooling, optimum mixing is more difficult to achieve.
Investigation of Two Advanced Cooling Mixing Concepts for a Rich Quench Lean Combustor
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, LA, June 4–7, 2001; Paper 01-GT-085. Manuscript received by IGTI, Dec. 2000, final revision, Mar. 2001. Associate Editor: R. Natole.
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Diers , O., Koopman , J., Fischer , M., and Hassa, C. (September 24, 2002). "Investigation of Two Advanced Cooling Mixing Concepts for a Rich Quench Lean Combustor ." ASME. J. Eng. Gas Turbines Power. October 2002; 124(4): 784–791. https://doi.org/10.1115/1.1473823
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