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Title: Aerodynamic Design Method and Experimental Investigation of a High-Load Supersonic Compressor Cascade
题目：超音速高负荷扩压叶栅气动设计方法及实验研究
Authors:YAN Tingsong, YAN Peigang, LIANG Zhuoming, CHEN Huanlong
作者：颜廷松，颜培刚，梁倬铭，陈焕龙
单位：哈尔滨工业大学
Journal of Thermal Science, 2024, 33(6): 2075-2088.
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摘要
Abstract: The high-load compressor plays an important role in further improving the performance of aero-engine. However, the complex shock waves in the cascade channel also bring more aerodynamic losses. This paper proposes a supersonic compressor cascade modeling method based on the theory of unique inlet flow angle, and the aerodynamic design and optimization of a cascade with inlet Mach number 1.85 are studied by combining the numerical optimization method and planar cascade experiment. The results show that pressure increase can be achieved by multiple shock waves which are obtained by the reflection of the leading edge detached shock wave in the initial supersonic cascade channel at the design point, which verifies the feasibility of the design method. After optimization, the aerodynamic performance of the cascade has been improved to different degrees at the design point and off-design point. When the static pressure ratio is 3.285, the total pressure recovery coefficient reaches 86.82% at the design point, which is on the advanced level of the same type of cascade. The experimental results of planar cascade schlieren and surface pressure measurement also verify the correctness of the simulation method, which provides useful references for the subsequent compressor design.
摘要：高负荷压气机对于进一步提高航空发动机性能具有重要作用。然而，叶栅通道内复杂的激波系也会带来更大的气动损失。本文基于唯一进气角理论提出一种超音速扩压叶栅的造型方法，并结合数值最优化方法和平面叶栅实验对来流马赫数1.85的叶栅开展气动设计与优化研究。结果表明，在设计点处，前缘激波在初始超声速叶栅通道内的反射获得的多个激波可以实现压力的增加，验证了设计方法的可行性。优化后的叶栅在设计点和非设计点的气动性能都得到了不同程度的改善。当静压比为3.285时，设计点总压恢复系数达到86.82%，在同类型叶栅中处于先进水平。所开展的平面叶栅纹影和叶表测压实验结果也验证了仿真方法的正确性，为后续压气机设计提供了有益参考。
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引用格式
YAN Tingsong, YAN Peigang, LIANG Zhuoming, CHEN Huanlong, Aerodynamic Design Method and Experimental Investigation of a High-Load Supersonic Compressor Cascade, Journal of Thermal Science, 2024, 33(6): 2075-2088.
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