基于吸力面叠加厚度的超跨声叶型优化设计

Supersonic and transonic airfoil optimization design based onsuperimposing thickness on suction surface

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。

To improve the optimization design quality of axial compressor airfoil,the parametric modeling method based on superimposing thickness on suction surface was proposed. The compressorairfoil optimization platform based on Kriging surrogate model and Differential Evolution algorithms wasdeveloped, and the control parameters of the suction surface were used as optimization variables tooptimize the performance of transonic and supersonic airfoils. The results showed that the parametricmodeling method based on superposing thickness distribution on suction surface can express the airfoilwell and was successfully applied to the optimization design platform. The loss of optimized transonic andsupersonic airfoils at design condition decreased by 10.66 % and 7.4%, respectively. The analysis showedthat as for the main characteristics of optimized transonic airfoil, the curvature of the profile near theleading edge of suction surface decreased, and the shock wave intensity decreased. Therefore, the shockwave loss and boundary layer loss decreased, the load at the middle and rear positions increased and theexpansion capacity of the expansion channel increased. The optimization of supersonic airfoil shouldconsider the profile of suction surface within the aft expansion passage additionally, because of moresignificant boundary layer influence. The position and width of throat can affect the chocking incidenceangle.