三维造型和非轴对称端壁在跨声速压气机中的应用

Application of 3D Blading and Non-Axisymmetric Endwall in a Transonic Compressor

为了提高跨声速压气机转子的气动性能,基于全三维数值模拟优化平台,对该转子先后进行了三维造型和非轴对称端壁造型,并对造型前后转子的性能和流场结构进行了对比分析。结果表明:三维造型和非轴对称端壁造型均可以改善跨声速压气机的气动性能,三维优化造型后近设计点压气机等熵效率提高了0.75%,非轴对称端壁优化造型后等熵效率进一步提高了0.3%,同时压气机的非设计工况性能也得到提升。三维造型改变了通道内激波位置,调整了负荷沿径向的分布,最终提高了压气机等熵效率。非轴对称端壁通过改变叶根截面叶片表面静压分布,使得叶根附近激波强度减弱并向下游移动,进而有效地降低了端壁区域的横向二次流强度。

In order to improve the aerodynamic performance of a transonic compressor rotor, based on three dimensional numerical simulation optimization platform, 3D blading and non-axisymmetric endwall con-touring has been carried out successively on this rotor and changes of performance and flow field were compared and analyzed. The results show that both 3D blading and non-axisymmetric endwall contouring can improve the aerodynamic performance of the transonic compressor. On near design point,the isentropic efficiency increased by 0.75%after 3D blading optimization and further increased by 0.3%after non-axisymmetric endwall contouring optimization,meanwhile the off-design performance of the compressor has also been improved. 3D blading chang-es the position of shock wave in the blade channel,adjusts the load distribution along the radial span,and final-ly increases the isentropic efficiency of the compressor. Through changing the static pressure distribution at the hub, non-axisymmetric endwall weakens the intensity of shock wave near the hub, and makes it move back-ward,and thereby reduces the intensity of transverse secondary flow in the endwall region.