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基于吸力面叠加厚度的超跨声叶型优化设计

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为提高轴流压气机叶型优化设计水平,提出了一种基于吸力面叠加厚度分布的参数化造型方法,结合基于Kriging代理模型与差分进化的代理优化方法开发了一套优化设计平台,并将吸力面控制参数作为优化变量,对某跨声与超声叶型进行性能优化.结果表明:基于吸力面叠加厚度分布的叶片造型方法能对叶型进行较好的表达,并成功应用在优化设计平台中.跨声、超声优化叶型在设计点损失分别降低了10.66％与7.4％.分析表明:跨声优化叶型的主要特征是吸力面型线前缘附近型线弯度降低,使得激波强度降低,激波损失与边界层损失降低,同时中后部位置处的负荷增大,扩张通道扩压能力增强;超声叶型优化由于边界层影响更显著,因此还需要更多考虑吸力面扩张通道区域型线;叶型喉部位置与喉部宽度会影响堵塞冲角的变化.
Supersonic and transonic airfoil optimization design based on superimposing thickness on suction surface
To improve the optimization design quality of axial compressor airfoil,the parametric modeling method based on superimposing thickness on suction surface was proposed.The compressor airfoil optimization platform based on Kriging surrogate model and Differential Evolution algorithms was developed,and the control parameters of the suction surface were used as optimization variables to optimize the performance of transonic and supersonic airfoils.The results showed that the parametric modeling method based on superposing thickness distribution on suction surface can express the airfoil well and was successfully applied to the optimization design platform.The loss of optimized transonic and supersonic airfoils at design condition decreased by 10.66％and 7.4％,respectively.The analysis showed that as for the main characteristics of optimized transonic airfoil,the curvature of the profile near the leading edge of suction surface decreased,and the shock wave intensity decreased.Therefore,the shock wave loss and boundary layer loss decreased,the load at the middle and rear positions increased and the expansion capacity of the expansion channel increased.The optimization of supersonic airfoil should consider the profile of suction surface within the aft expansion passage additionally,because of more significant boundary layer influence.The position and width of throat can affect the chocking incidence angle.

axial compressorsupersonic and transonic airfoilsuction surfacethickness distributionparametric modeling methodKriging surrogate optimizationaerodynamic optimization

刘帅鹏、耿少娟、金芸、李鑫龙、张宏武

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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

中国科学院轻型动力创新研究院,北京 100190

中国科学院先进能源动力重点实验室,北京 100190

中国科学院大学航空宇航学院,北京 100049

中国科学院大学工程科学学院,北京 100049

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轴流压气机 超跨声叶型 吸力面 厚度分布 参数化造型方法 Kriging代理优化 气动优化

国家科技重大专项国家科技重大专项

2017-Ⅱ-0007-00212017-H-0006-0020

2024

10.13224/j.cnki.jasp.20210577

航空动力学报
中国航空学会

航空动力学报

CSTPCD北大核心
影响因子：0.59
ISSN：1000-8055
年,卷(期)：2024.39(5)
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