Numerical Bipropellant Thruster Simulation with Hydrazine and NTO Reduced Kinetic Reaction Model
Numerical Bipropellant Thruster Simulation with Hydrazine and NTO Reduced Kinetic Reaction Model
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DOI：
10.2514/6.2009-452
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发表时间：
2009-01
期刊：
影响因子：
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通讯作者：
Kaori Ohminami;H. Ogawa;K. Uesugi
中科院分区：
文献类型：
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作者：
Kaori Ohminami;H. Ogawa;K. Uesugi
对气膜冷却双组元推力器内的燃烧流场进行了数值模拟.薄膜冷却双组元推力器模型包括肼燃料和四氧化二氮氧化物（NTO）氧化剂的61个基元反应的简化详细动力学模型。该动力学反应模型最初由245个基元反应组成，并被开发用于CFD模拟。双组元推力器模型考虑了液滴运动和蒸发机理，可以模拟湍流流场下的燃气生成过程。流动模拟结果详细地揭示艾德火焰结构和气膜冷却机理，并与实验结果相吻合，能较好地解释气膜冷却干熄机理。
A combustion flow inside a film -cooled bipropellant thruster was simulated numerically. The film -cooled bipropellant thruster model include d a reduced detail kinetic reaction model of hydrazine fuel and di -nitrogen tetroxide (NTO) oxidizer composed of 61 elementary reactions. This kinetic reaction model had been origin ally composed of 245 elementary reactions and was developed to be available for CFD simulations. Also bipropellant thruster model included droplet motion and evaporation mechanism so that it could simulate the gas generation with turbulent flow field. The flow simulation results show ed the flame structure and film -cooled mechanism in detail and could explain the film -cooling dry out mechanism in accordance with experimental results.