基于相对流面理论的液体火箭发动机泵内部流动计算  

Calculation of internal flow in pump of liquid rocket engine based on theory of relative stream surface

作　　者：马冬英[1] 雷宗琪[1] 梁国柱[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2013年第3期583-590,共8页Journal of Aerospace Power

摘　　要：应用相对流面理论对某液体火箭发动机离心泵内叶轮机械部件的内部流动进行计算和分析.流面的求解采用流线曲率法.根据不同部件内的流动数值模拟编制了模块化计算程序,使各部件的计算相对独立.不同部件之间采用混合平面法进行处理,将非定常问题转化为定常问题,简化计算.黏性的影响通过几种损失系数进行修正.数值计算的结果显示诱导轮和离心叶轮增加了液体的压强,而导流通道主要改变了液体的流动方向。The theory of relative stream surface was applied to calculate and analyze the internal flow in a centrifugal pump of a liquid rocket engine.Streamline curvature method was used for calculation.Modularized calculation programs were developed to simulate the flow process in different parts of the pump,which allowed the calculation of every part to be conducted independently.The interaction between different parts was dealt with by the idea of mixing plane to convert the unsteady problem to steady problem.The effect of viscosity was corrected by several loss coefficients.The result shows that the inducer and the centrifugal impellers increase the pressure while the guide vane remains only changes the direction of the velocity,which consist with theoretical analysis.

关 键 词：液体火箭发动机 离心泵 相对流面理论 流线曲率法 混合平面法 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] V212