风扇转子叶型侵蚀前缘再造型优化设计

Design Optimization of Remodeling Fan Rotor Blade Airfoil with Leading-Edge Erosion

针对前缘侵蚀风扇转子叶型的优化设计问题,以某小型大涵道比涡扇发动机前缘侵蚀风扇转子叶片50%叶展截面叶型为研究对象,开展侵蚀前缘再造型的多工况、多目标优化设计。选取0°、+4°和+6°攻角作为参考工况,应用层次分析法分别建立各工况的权重,通过商业软件NUMECA中FINE/Design3D模块开展大半径环形叶栅优化设计。结果表明:前缘优化显著改善了前缘侵蚀叶型的气动性能,优化后叶型不仅能够恢复60%以上的由于前缘侵蚀导致的总压损失系数增大,而且在+4°攻角下总压损失比原始叶型的减小了4.3%。此外,前缘优化对叶型吸力面前缘分离泡的产生和生长具有一定的抑制作用,使其附面层厚度保持较为良好的发展状态,有效地减小了附面层内部的流动损失。

Taking the eroded leading edge airfoil in the 50%height of fan rotor for a small turbofan engine with high bypass ratio as research object.The research for multi-condition and multi-objective optimization design of the eroded leading edge remodeling was carried out.0°,+4°and+6°incidence angles are selected as the reference working conditions and the analytic hierarchy process is used to establish the weights of each working condition.The FINE/design 3D module of NUMECA was used to optimize the design of large radius annular cascades.Numerical calculation results show that leading edge optimization can significantly improve the aerodynamic performance of the eroded leading edge airfoil.The optimized airfoil can not only recover more than 60%increase in the total pressure loss coefficient caused by leading edge erosion,and the total pressure loss under+4°incidence angle is reduced by 4.3%compared with the original airfoil.The optimization of the leading edge has a certain inhibitory effect on the generation and growth of the separation bubble in the suction side of leading edge,so that the thickness of the boundary layer maintains a good development state and it effectively reduces the flow loss inside the boundary layer.