零预旋涡轮动叶吸力面无遮盖段内凹型线激波损失抑制方法研究  

A Shock Loss Reduction Method for a Zero Inlet Swirl Turbine Rotor Using a Suction Side Concave Profile

作　　者：周庆晖 赵巍[1,2,3,4] 隋秀明 赵庆军[1,2,3,4] 徐建中[1,2,3,4] ZHOU Qing-Hui;ZHAO Wei;SUI Xiu-Ming;ZHAO Qing-Jun;XU Jian-Zhong(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;Beijing Key Laboratory of Distributed Combined Cooling Heating and Power System,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学航空宇航学院,北京100049 [3]中国科学院轻型动力创新研究院,北京100190 [4]中国科学院工程热物理研究所分布式冷热电联供系统北京市重点实验室,北京100190

出　　处：《工程热物理学报》2022年第4期939-944,共6页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(No.2017-III-0010-0036);国家自然科学基金面上项目(No.51776198)。

摘　　要：为降低以气流加速为主要做功手段的零预旋涡轮动叶激波损失,提出了以折转角为控制变量的吸力面无遮盖段内凹型线量化设计方法。根据激波等强度时波系总损失最小的原理,建立内凹型线诱导激波和吸力面尾缘外伸激波等强度气流关系方程组,求解内凹型线最优折转角,实现激波等强度设计。内凹型线具有最优折转角时,内凹型线诱导激波有效减少吸力面尾缘外伸激波的波前马赫数及气流折转角,激波系总压损失系数降低,叶栅总压恢复系数提高1.5%,表明该方法能够用于低激波损失叶型吸力面内凹型线量化设计。The trailing edge shock induces significant aerodynamic losses in a zero inlet swirl turbine rotor(ZISTR) whose power output is mainly obtained by the flow acceleration. To reduce the shock loss for a ZISTR, this paper presents a quantitative design method, using a concave curve on the uncovered suction side. The suction side concave curve is designed based on the deflection angle across it. Previous studies have proved a principle that, for a system of multiple shocks, the minimum shock loss is obtained when their strengths are equal. According to this principle, the deflection angle across concave curve can be optimized so that the strength of a concave curve induced shock is equal to that of a suction side trailing edge shock. In order to make the strengths of these two shocks equal, this paper builds a set of equations which describe the Mach number and flow deflection angle of these two shocks to solve the exact value of the optimal deflection angle across concave curve. It is found that, for an improved ZISTR cascade employing the concave curve with optimal deflection angle,the concave curve induced shock reduces the Mach number upstream of the suction side trailing edge shock and the flow deflection angle across it. As a result, the total pressure loss coefficient of shock system decreases, and the total pressure recovery coefficient of cascade increases by 1.5%. This investigation indicates the effectiveness of the quantitative design method using the concave curve with optimal deflection angle for shock loss reduction.

关 键 词：零预旋涡轮动叶 吸力面无遮盖段 内凹型线 激波等强度设计 激波损失 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]