Yu.Meng , Hongbin.Gu ，Jingheng Zhuang, Wenming Sun, ZHanbiao Gao ,Huan Lian ,Lianjie Yue, Xinyu Chang

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_3180980

This experiment was carried out on a direct-connected supersonic combustion test bench. High-speed photography was used to record the CH* emission during ignition and extinguishing of the kerosene from wall jet, under a Mach number of 2.5 airflow, and the flame evolution process of kerosene was captured. The experiment was shown that the ignition initial core is located at the cavity step, but not the place of spark. And then gradual backward extent to the whole cavity. Kerosene flame combustion shows a non-steady state and then gradually contracts, when the flame is blown out. At the same time, this paper also studied the flame stability during the process of Ma2.5 at the entrance of the combustion chamber. The shock waves in flame was captured by schlieren technique. An equilibrium flame pattern of shock wave and flame was found in the experiment. In the state of stable flame, shock waves near the kerosene jet orifice can promote atomization and blending, and the combustion chamber pressure with stable flame makes the shock waves stable near the kerosene jet orifice, thus forming the flame stability model.

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In Categories: HiSST 2018, Hypersonic Propulsion, Propulsion, Propulsion Systems and Components, Testing and Evaluation, Thermal and Energy Management Systems
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