跨声压气机动叶周向弯曲的数值优化设计  

Numerical Optimization Design of Circumferentially Curved Transonic Compressor Rotor

作　　者：伊卫林[1] 黄鸿雁[1] 韩万金[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空动力学报》2006年第3期480-484,共5页Journal of Aerospace Power

基　　金：高校博士点基金资助(20030213022)

摘　　要：开发了求解雷诺平均N-S方程的三维流场模拟程序及数值优化程序,对流场求解程序进行了实验验证,并对跨声压气机动叶积叠线周向弯曲进行优化设计。优化结果表明压气机动叶弯曲可以有效地改变流场内的三维激波结构,削弱尾迹损失。绝热效率提高约0.59%。并且改善了压气机变工况性能。A flowfield simulation code was developed based on Reynolds-averaged Navier-Stokes equations and validated by experimental data. A numerical optimization code was developed and applied to the optimization design of a circumferentially curved transonic compressor rotor. Results indicate that the circumferential curving can effectively change the three dimensional shock wave structures and weaken wake losses. Optimized blades improve adiabatic efficiency approximately 0.59% and possess fine off-design performance.

关 键 词：航空 航天推进系统 压气机动叶 周向弯曲 三维激波结构 优化设计 

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]