采用排间界面静压约束伴随方法的多级压气机叶片优化  

Blade shape optimization of multistage compressor using adjoint method with static pressure constraint at interfaces between rows

作　　者：唐方明[1] 余佳[2] 李伟伟[2] 季路成[2] 

机构地区：[1]中国航空工业集团公司中国航空动力机械研究所,湖南株洲412002 [2]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2015年第8期1869-1874,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(51176012)

摘　　要：为解决伴随优化应用在多级压气机中出现的优化工况点漂移问题,在前期薄层N-S方程伴随方法基础上,对目标函数——出口熵增不仅施以质量流量、总压比约束,还添加排间界面静压展向分布作为新的约束条件.以某5级压气机为对象,对其中第1级转、静叶分别在首1.5级和全5级压气机环境下进行了优化.结果表明,施加排间界面静压展向分布约束能够显著解决优化工作点漂移问题,优化后5级压气机的效率提高0.4个百分点.To solve the problem with the drift of operation condition during the optimization procedure when adjoint method applied in multistage compressor,based on the previous development work of multistage compressor blades optimization design using adjoint method and thin shear-layer N-S equations,the entropy production was selected as the objective function with given mass flow rate and total pressure ratio as imposed constraints,a new constraint was introduced,namely,the spanwise static pressure distribution at the interfaces between rows was imposed.Taking one 5stage compressor as a test case,the new method was applied at inter-row interfaces behind the rotor and the stator of the first stage in environment of the first 1.5stage and the whole 5stage compressor.The results show that the drift problem of the operation condition during optimization procedure is resolved successfully by applying the constraint on spanwise static pressure distribution at the interfaces between rows and the efficiency of 5stage compressor is got 0.4%improving.

关 键 词：多级压气机 伴随方法 优化设计 排间界面 压强分布约束 

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]