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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。
On the basis of the non-inspiration leaf-type optimization design platform, the boundary conditions at the aspirating position in the flow field calculation process of the cascade are treated, and an optimized design platform of the adsorption fan / compressor blade is established. The optimization design platform is used to optimize a high-subsonic aerofoil. In the process of optimization, the parameterization of the aerofoil is based on the initial aerofoil modification method. In addition to taking the leaf-type control parameter in the parameterization of the aerofoil as the design variable, The location is also used as a design variable with an inspiratory coefficient of 0.01 and unchanged. The results of NUMECA show that the total pressure loss coefficient of the optimized blade is 0.0195 and the diffusion coefficient is 0.676. Compared with the pre-optimization, the total pressure loss coefficient is reduced by 54% and the diffusion factor remains unchanged. The inflection point appears at the tail of the optimized blade pressure surface, and the flow accelerates and decompresses before the inflection point. The disadvantage is that the blade tail load is reduced, but also the flow separation is restrained and the loss is reduced.