Hybrid rocket technology is known since the 30's and a large number of experimental, fundamental and applied research works covers it. It still suffers from a lack of chemical description and of detailed numerical simulation of core phenomena. Several numerical codes have emerged to simulate hybrid rocket combustion chamber but with limited consideration for detailed chemistry. A new 2-D transient reactive numerical code has been proposed in the goal of using detailed chemical mechanisms for both pyrolysis and combustion reactions (over 1000 species and 10000 reactions). The direct computation of such mechanisms is too much time consuming. In order to speed up the computation, methodologies for treating chemistry have been set up. In this paper, one of the methodologies is explained and validated trough several validation cases. With all methods combined, the results show an error less than few percents on the ignition delay of the flame and a computational time cut by a factor higher than 1.
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