高马赫数超声压气机转子叶型优化设计

发布时间：2019-04-16 17:01

【摘要】：为进一步提高压气机叶尖轮缘速度和增压比,将唯一进气角原理和数值最优化技术用于叶型设计,获得两个高马赫数、高压比、低损失的"S"形超声压气机叶型。首先根据压气机流动机理,提出超声压气机叶栅的性能指标;然后通过吸力面叠加厚度的方式生成初始叶型,保证叶栅的来流马赫数和唯一进气角;最后采用基于修改量的叶型参数化方法,以给定总压比为约束条件,以总压损失系数最小为目标对初始叶型优化。设计结果表明:在设计点,叶栅1和叶栅2的总压损失系数分别为0.119和0.158;在高来流马赫数条件下,超声叶栅需采用大稠度设计才能实现多道斜激波加一道正激波增压;在叶型吸力面前端构造一个斜坡也可增加叶栅通道内的斜激波数量;平直的吸力面后段有利于削弱激波对附面层干扰,将平直吸力面后段与钝尾缘(或翘尾缘)相结合可有效抑制附面层分离,减小尾迹区。
[Abstract]:In order to improve the speed and pressure ratio of blade tip of compressor, the principle of unique inlet angle and numerical optimization technique are applied to the design of blade profile. Two "S"-shaped ultrasonic compressor blades with high Mach number, high pressure ratio and low loss are obtained. According to the compressor flow mechanism, the performance index of the ultrasonic compressor cascade is proposed, and then the initial blade shape is generated by adding the thickness of the suction surface to ensure the Mach number and the unique inlet angle of the cascade. Finally, the initial blade profile is optimized with the objective of the minimum total pressure loss coefficient and the given total pressure ratio as the constraint condition by using the parameterization method based on the modifiers. The design results show that the total pressure loss coefficients of cascade 1 and cascade 2 are 0.119 and 0.158 at the design point, respectively. Under the condition of high flow Mach number, it is necessary to adopt high consistency design to realize multi-channel oblique shock wave plus one normal shock wave pressurization, and to construct a slope in front of blade suction can also increase the number of oblique shock wave in cascade channel, and the structure of a slope in front of blade suction can also increase the number of oblique shock waves in cascade channel. The rear section of the flat suction surface is beneficial to weaken the interaction between the shock wave and the boundary layer. The separation of the boundary layer and the wake region can be effectively suppressed by combining the rear segment of the flat suction surface with the blunt trailing edge (or trailing edge).
【作者单位】：中国空气动力研究与发展中心计算空气动力研究所;南京航空航天大学能源与动力学院;
【基金】：国家自然科学基金(11572339)
【分类号】：V233

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