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首页> 外文期刊>Propellants, Explosives, Pyrotechnics >Study on the Initiation Mechanism of Non-Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet
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Study on the Initiation Mechanism of Non-Premixed Shock Induced Combustion in Supersonic Propellant Gas Jet

机译：超声推进剂气体射流中未预混冲击诱导燃烧的起始机理研究

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摘要

The reflection of a supersonic propellant gas jet always happens during the firing of the weapon system of aircraft. The reflection induces complex non-premixed shock induced combustion. It is of great importance to investigate the initiation mechanism of the combustion in the supersonic jet of propellant gas. The mechanism is vital for the design of any suppression method of the secondary combustion. To investigate the combustion in the reflected supersonic jet, a solid propellant combustion model and a numerical model based on compressible multispecies Navier-Stokes equations are established. A detailed reaction mechanism consisting of 9 species and 12 reactions is utilized for the combustion of the propellant gas. Based on the models, the supersonic precursor flow field and the supersonic propellant gas jet flow are obtained and discussed. A secondary jet is observed which has not been reported before. A sandwich structure is proposed to reveal the initiation of the combustion. The oxygen supply in the secondary jet is found to be dominated by a vortex. An inert gas atmosphere can be adopted to suppress the mass transfer at the contact surface. Special devices could be designed to suppress the formation of the vortex in the secondary propellant jet.
机译：超声波推进剂气体喷射的反射始终在飞机武器系统的烧制过程中发生。反射诱导复杂的非预混冲击诱导燃烧。研究推进剂的超音速射流中燃烧的启动机制非常重要。该机制对于设计二次燃烧的任何抑制方法至关重要。为了研究反射超声波射流中的燃烧，建立了基于可压缩多数Navier-Stokes方程的固体推进剂燃烧模型和基于可压缩的Multipecies Navier-Stokes方程的燃烧。由9种和12个反应组成的详细反应机理用于推进剂气体的燃烧。基于模型，获得了超音速前体流场和超声波推进剂气流流动并讨论。观察到尚未报道的二次射流。提出了夹层结构，揭示了燃烧的启动。发现次级射流中的氧气供应由涡旋支配。可以采用惰性气体气氛来抑制接触表面处的质量传递。可以设计特殊装置来抑制二级推进剂射流中的涡流的形成。

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