考虑静叶封严泄漏对压气机端区影响的三维叶片优化

鉴于静叶叶根封严蓖齿间隙的泄漏对压气机端区所产生的不利影响,取某带静叶封严结构的双级轴流压气机为研究对象,采用遗传算法对其进行了气动数值优化.优化自变量为所选双级轴流压气机的后面级静叶近轮毂区叶型的安装角和前缘角,优化目标为极大化该双级轴流压气机的等熵效率.优化后,双级轴流压气机设计点的等熵效率提高了约0.2个百分点.所优化的静叶近轮毂处呈现出了明显的端弯效果.双级轴流压气机性能改善的主要原因是,通过对后面级静叶根部叶型的调整,使其端区来流的攻角值落在了该叶型的最优设计攻角的附近.

Three-dimensional blade optimization considering effect of stator seal leakage on end-wall in compressor

Considering the negative effect of the leakage of the labyrinth seal gap close to the stator root on the end-wall in the compressor, a two-stage axial compressor of the stator seal structure was chosen as the research subject. Genetic algorithm (GA) was applied to conduct numerical aerodynamic optimization of this two-stage axial compressor. The optimization variables included the stagger angles and the leading-edge angles of the airfoils close to the hub of the rear-stage stator, and the optimization object was to achieve the maximum isentropic efficiency of the two-stage axial compressor. After the optimization, the isentropic efficiency of the two-stage axial compressor in the design point increased by 0.2 percentage points, and the rear-stage stator obviously showed the end-bend blading close to the hub. The main reason for the improvement of the two-stage axial compressor performance is that after the root airfoils of the rear-stage stator have been modified by the optimization, the incidences of the upstream flow close to the end-wall are located close to the optimal design incidences of these airfoils.