基于S_1,S_2流面理论的液体火箭发动机涡轮内部流场计算  

Calculation of the internal flow for turbine of liquid rocket engine based on the theory of S_1,S_2 stream surface

作　　者：马冬英[1] 梁国柱[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2008年第4期401-406,共6页Journal of Propulsion Technology

摘　　要：应用S1,S2流面理论对某大型液氢/液氧火箭发动机涡轮泵的两级轴流式涡轮内部跨声速流场进行计算和分析。流面的求解采用流线曲率法。将混合平面法的思想用于流线曲率法的求解过程中,对动、静叶排之间的相互干扰进行处理,将复杂的非定常问题简化为定常问题,从而简化计算。粘性的影响通过几种损失系数进行修正。计算结果较好地描述了涡轮内部的流动情况,为进一步完善涡轮设计、提高涡轮性能提供了理论依据。The theory of S1 and S2 stream surface was applied to calculate and analyze the internal transonic flow field for a two-stage axial turbine used in turbopump for liquid rocket engine. Streamline curvature method was used for calculation. The interaction between the stator and the rotor was dealt with the idea of mixing plane, and then the unsteady problem was simplified to the steady problem. The influence of viscosity was corrected by several loss coefficients. The result of calculation describes the internal flow of the turbine well and provides a theoretical basis for improving the design and performance of the turbine.

关 键 词：液体推进剂火箭发动机 涡轮 S1 流面+ S2流面+ 跨音速流 涡轮泵 

分 类 号：V434.211[航空宇航科学与技术—航空宇航推进理论与工程]