通流优化是提升压气机性能的重要途径，针对燃气轮机的环境/工况适应性问题，设计目标的表述和优化变量选取至关重要。本文借助三维数值模拟手段和寻优算法，研究了燃气轮机压气机叶片最大挠度、最大挠度位置、最大厚度、最大厚度位置等参数对叶片变工况性能的影响规律。以拓宽三维叶片攻角适应性为目标，开展了三维叶片的优化设计，分析和总结了不同截面叶型参数的分布特征，探讨了宽适应性压气机叶片表面的气动布局和损失机理。研究结果表明:在两倍损失攻角范围内，中弧线挠度大小对气动损失的影响要大于挠度位置，最大厚度相对位置的影响则要大于最大厚度值，优化后叶片在零攻角与正负6°攻角下的总压损失降幅分别达到3.52%、9.31%、11.32%。

Through-flow optimization is an important way to improve the performance of compressor, and the formulation of design objectives and the selection of optimization variables are crucial for the environmental/operating condition adaptability problem of gas turbines. In this paper, with the help of CFD and optimization algorithms, the influence laws of parameters such as maximum camber, maximum camber position, maximum thickness, and maximum thickness position of gas turbine compressor blades on the performance of blades in variable operating conditions are investigated. With the objective of broadening the adaptability of 3D blade angle of attack, the optimization design of 3D blade is carried out, the distribution characteristics of different section blade parameters are analysed and summarized, and the aerodynamic configuration and loss mechanism of the surface of wide-adaptable compressor are explored. The research results show that, in the range of two times loss incidence, the influence of mid-arc deflection size on aerodynamic loss is greater than camber position, and the influence of maximum thickness relative position is greater than maximum thickness value, and the total pressure loss reduction of the optimized blade of the incidence at zero and plus or minus 6° reaches 3.5218%, 9.3098%, and 11.3246%, respectively.

国家自然科学基金项目（面上项目，重点项目，重大项目）