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Etude numerique et parametrique de la combustion de particules d'aluminium

机译:铝颗粒燃烧的数值和参数研究

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Several numerical models have been investigated to study the reactivity of aluminium particles coming from the com- bustion of solid propellants in spatial launchers. The Law model has been rapidly selected as it yields a continuous model from an aluminium drop to an oxide drop. The model also gives the residue size at the end of the combustion process. This could explain the scaling observed in the rocket engines. In order to study the coupling between the flow and the combustion, the combusion of aluminium drops has been widely analyzed with oD computation. The main mechanisms of the combustion process have been identified.
机译:已经研究了几种数值模型来研究空间发射器中固体推进剂燃烧产生的铝颗粒的反应性。已迅速选择了Law模型,因为它产生了从铝滴到氧化物滴的连续模型。该模型还给出了燃烧过程结束时的残留物尺寸。这可以解释在火箭发动机中观察到的结垢。为了研究流动与燃烧之间的耦合,已经通过oD计算广泛地分析了铝滴的燃烧。已经确定了燃烧过程的主要机理。

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