宽裕度超声叶型气动优化设计  

Wide stability margin aerodynamic optimization design of supersonic profile

作　　者：韩露 周正贵[1] 陈劲帆 HAN Lu;ZHOU Zhenggui;CHEN Jinfan(College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2020年第6期1247-1256,共10页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅱ-0001-0013)。

摘　　要：通过与德国航天局设计的超声预压缩叶型PAV-1.5试验数据比对,确定高精度超声叶栅流场计算方法,研究表明:根据激波位置分段调整流管厚度可提高计算与试验结果的一致性。为提高超声叶栅稳定工作裕度并保证设计点性能,建立根据目标裕度估算喘点反压方法和优化设计方法。对两个超声叶型进行多目标优化,优化结果表明:优化叶栅可减小设计工况槽道激波入射角、减小激波及激波附面层干扰损失;气动喉道前移、结尾正激波后移,提高叶栅耐反压能力。两个优化叶型在保持总静压比不变的前提下,稳定裕度均达到设计目标,设计点损失也有所下降。By comparing with the experimental data of PAV-1.5 designed by German space agency, the calculation method of flow field in supersonic cascade with high accuracy was determined. The results showed that the consistency between the calculation and the experimental results can be improved by adjusting the thickness of the flow tube according to the position of shock wave. In order to improve the stability margin and ensure the performance at design point of supersonic cascade, the back pressure estimation method and optimization design method based on target margin were established. The multi-objective optimization of the two supersonic blades was carried out. The optimization results show that the optimal cascade can reduce the incident angle of the shock wave at design point, and cut down the shock wave and shock wave boundary layer interference loss. The aerodynamic throat moving forward and the terminal normal shock wave moving backward can improve the shock-holding capability. Under the premise of keeping the total and static pressure ratio unchanged, the stability margins of the two optimal blade profile reached the design goal, and the loss at design point also decreased.

关 键 词：压气机叶栅 超声叶型 稳定工作裕度 多目标优化 耐反压能力 

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]