摘要
在无吸气叶型优化设计平台的基础上,对叶栅流场计算程序中吸气位置处边界条件进行处理,建立了吸附式风扇/压气机叶型优化设计平台。应用该优化设计平台对某高亚声速叶型进行了优化,优化过程中叶型参数化采用初始叶型叠加修改量方法,除将叶型参数化中的叶型控制参数作为设计变量外,吸气位置也作为设计变量,吸气系数为0.01且保持不变。NUMECA计算结果表明:优化叶型的总压损失系数为0.0195,扩散因子为0.676;与优化前相比,优化后总压损失系数减小了54%,扩散因子保持不变。该优化叶型压力面尾部出现拐点,拐点前流动加速减压,缺点是减小了叶型尾部负荷,但也抑制了流动分离,减少了损失。
By modifying the cascade flow solver to consider the effect of suction,an optimization design tool existed for profiles without suction can be used to design axial aspirated fan/compressor profiles.A high-subsonic profile is optimized by the tool,during the optimization,new profiles are created by adding smooth perturbations to the original profile and suction hole location as well as variables related to profile parameterization is served as design variables while the ratio of suction mass flow to inlet mass flow is kept 0.01.Results from NUMECA show that the optimum profile with total pressure loss coefficient of 0.0195 and diffusion factor of 0.676 is obtained and that total pressure loss coefficient is reduced by 54% and diffusion factor kept the same compared to the original profile.One notable feature of the optimum profile is the inflection point at the back part of pressure surface,which contributes to the low loss and the negative aft loading.
出处
《航空发动机》
2013年第3期46-48,58,共4页
Aeroengine
关键词
吸附式风扇
压气机
附面层吸气
优化设计
低损失
拐点
axial aspirated fan/compressor
boundary layer suction
optimization design
low-loss
inflection point
