超音速复速级涡轮的气动设计改进  

Aerodynamic redesign of supersonic Curtis-stage turbine

作　　者：林奇燕[1] 金志磊 王磊[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2014年第1期65-70,共6页Journal of Rocket Propulsion

摘　　要：采用数值模拟方法对某液体火箭发动机超音速复速级涡轮进行了流场分析。根据分析结果对两列动叶的叶型进行了改进设计:第一列动叶栅的改进采用自由旋流法,通过等通道的叶栅流道设计,减弱了激波对附面层的干扰,有效抑制了流道内的流动分离;第二列动叶栅的改进采用参数化叶片造型法,型线用具有局部修改能力和保凸性较好的Bezier曲线表示,通过减小入口攻角降低了分离损失。数值模拟结果表明,改进后的复速级涡轮内部流动特性改善显著,分离损失明显减小,效率提高了5%以上。3D flow field analysis of the supersonic Curtis-stage turbine in a liquid rocket engine was conducted by mean of numerical simulation. On the base of analysis result, the blade profile of two-row rotor was redesigned. The blade cascade of the first row rotor was redesigned with the method of free vortex flow, which weakened the interactive effect of shock wave on boundary layer and restrained the flow separation inside the cascade with the constant flow channel design. The pa- rameterized blade shape construction method was adopted in the redesign of the second row rotor blade cascade, which was presented by Bezier curve. The separation loss was declined by reducing the intake incidence. The results of the numerical simulation indicate that the characteristic of internal flow in the redesigned Curtis-stage turbine is improved remarkably, the separation loss is reduced ob- viously and the turbine efficiency is increased by more than 5%.

关 键 词：超音速涡轮 复速级涡轮 气动设计 数值模拟 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]