This study presents the use of a genetic algorithm to produce a new reduced chemical kinetic reaction mechanism to simulate aviation fuel combustion under various operating conditions. The mechanism is used to predict the flame structure of a aviation fuel/O2/N2 flame in both spatially homogeneous and one-dimensional premixed combustion. Complex hydrocarbon fuels, such as aviation fuel, involve large numbers of reaction steps with many species. As all the reaction rate data is not well known, there is a high degree of uncertainty in the results obtained using these large detailed reaction mechanisms. In this study a genetic algorithm approach is employed for determining new reaction rate parameters for a reduced reaction mechanism for the combustion of aviation fuel/air mixtures. The genetic algorithm employed incorporates both perfectly stirred reactor and laminar premixed flame data in the inversion process, thus producing an efficient reaction mechanism. This study provides an optimised reduced aviation fuel/air reaction scheme whose performance in predicting experimental major species profiles and ignition delay times is not only an improvement on the starting reduced mechanism but also on the full mechanism.
A Novel Approach to Mechanism Reduction Optimisation for Aviation Fuel/Air Reaction Mechanism Using a Genetic Algorithm
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Elliott, L, Ingham, DB, Kyne, AG, Mera, NS, Pourkashanian, M, & Wilson, CW. "A Novel Approach to Mechanism Reduction Optimisation for Aviation Fuel/Air Reaction Mechanism Using a Genetic Algorithm." Proceedings of the ASME Turbo Expo 2004: Power for Land, Sea, and Air. Volume 1: Turbo Expo 2004. Vienna, Austria. June 14–17, 2004. pp. 1-10. ASME. https://doi.org/10.1115/GT2004-53053
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