旋转燃烧室中燃烧性能研究

On Combustion of Liquid Monopropellant in Rotating Combustion Chamber

针对燃烧室本身旋转及使用单组元液体推进剂的特点，对此两相湍流反应流，在质量、动量和能量传输基础上，建立了在旋转燃烧室中单组元液体推进剂雾化燃烧过程计算的模型和边界条件．模型计算采用了ＳＩＭＰＬＥ算法和ＰＳＩＣ算法，得到气相燃料的速度场和浓度场．实验得到反映燃烧效率的特征速度比，与计算浓度场反映的燃烧效率比较结果一致．本文不仅反映了燃烧室旋转时，强化了燃烧，提高了效率，而且说明此研究可用于预示与分析类似问题．

After very careful search,the authors have not found in the open literature any theoretical analysis or experimental data concerning combustion performance of rotating combustion chamber employed in US M K48 torpedo.Rotating combustion chamber of MK48 is just one kind of such chamber. The authors propose a spray combustion computation model that is believed to be applicable to any liquid monopropellant rotating combustion chamber. With this model,the authors compute the velocity field and mass fraction field of fuel evaporated in a specific rotating combustion chamber.The computed mass fraction field allows the authors to determine combustion efficiency,which is in agreement with combustion efficiency determinable from cxpcrimcntally measured characteristic velocity ratios.The establishment of the authors' computation model includes essentially two considerations:(1)the problem is simplified into a two-phase turbuleat reacting now;(2)transfer of mass,momentum,and energy is taken into account.