轴流压气机叶片与机匣处理一体化优化设计  

Integrated design optimization of blade and casing treatment in axial compressor

作　　者：范忠岗 巴顿 邱佳慧 杨晨 杜娟[1,2,3,4] FAN Zhonggang;BA Dun;QIU Jiahui;YANG Chen;DU Juan(Advanced Gas Turbine Laboratory,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;Key Laboratory of Advanced Energy and Power,Chinese Academy of Sciences,Beijing 100190,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院工程热物理研究所先进燃气轮机实验室,北京100190 [2]中国科学院先进能源动力重点实验室,北京100190 [3]中国科学院轻型动力创新研究院,北京100190 [4]中国科学院大学航空宇航学院,北京100049

出　　处：《航空动力学报》2024年第7期205-216,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51922098);国家重大科技专项(2017-Ⅱ-0004-0017,J2019-Ⅱ-0020-0041)。

摘　　要：针对一台低速轴流压气机搭建了叶片与机匣处理一体化优化设计平台,基于自由变形技术关联设计参数与工程参数,实现多目标优化.综合考虑效率和裕度指标,在峰值效率不降的情况下获得了7.21%的裕度拓宽量.针对最优方案,分析了叶顶堵塞及损失分布,探讨了叶片与机匣处理一体化优化设计的扩稳机理.研究发现:叶片弯掠和机匣处理组合作用下,最大堵塞位置由24.7%叶顶轴向弦长后移至33.6%叶顶轴向弦长,最大损失位置由21.4%叶顶轴向弦长后移至30.6%叶顶轴向弦长,叶顶泄漏涡的抑制和低能堵塞区的消除是一体化优化设计扩稳的主要原因.An integrated optimization design platform of blade and casing treatments in a low-speed axial compressor was constructed.A practical partitioning approach for free-form deformation(FFD)parameterization combined with engineering parameters was applied to achieve multi-objective optimization.Taking both efficiency and stall margin into consideration,the optimal design improved the stall margin by 7.21%with negligible peak efficiency variation.After analysis and calculation of blockage and loss distribution,the influence mechanism on stall margin and efficiency was further studied.Results showed that with the combined effected of deformed blade and casing treatment,the location of peak blockage moved downstream from 24.7%rotor tip chord to 33.6%rotor tip chord,and the location of peak efficiency moved downstream from 21.4%rotor tip chord to 30.6%rotor tip chord.The main reason for stall margin improvement was attributable to the suppression of tip leakage and the elimination of low energy blockage flow at tip region.

关 键 词：轴流压气机 自由变形技术 一体化优化设计 裕度拓宽 堵塞 熵产率 

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]