摘要
以某涡扇发动机风扇叶片亚声叶型为研究对象,参考美国标准大气推广委员会(COESA)的大气模型,对原始叶型和两种前缘侵蚀叶型在5个大气高度下进行数值模拟计算,探究在高空低雷诺数环境下前缘侵蚀对亚声叶栅流动特性的影响。结果表明:0°攻角下低雷诺数条件削弱了气流在前缘处对前缘形貌的敏感程度,使得3种叶型前缘处压力分布、吸力面边界层的流动分离与转捩、尾缘分离程度均趋于一致,最终表现为由前缘侵蚀引起的总压损失增大量随着雷诺数降低而减小,3种叶型的总压损失系数和压比趋于一致。而在4°攻角下,前缘侵蚀在低雷诺数下可以促进转捩的发生,减小尾缘分离程度,进而使得总压损失小于0°攻角的情况,在进口马赫数为0.6时降低了23.6%,在进口马赫数为0.8时则降低了41.2%。
Taking the subsonic airfoil of a turbofan engine fan blade as the research object,numerical simulation of the original airfoil and two leading edge erosion airfoils at five atmospheric heights was carried out with reference to the Committee on Extension to the Standard Atmosphere(COESA)standard atmospheric model,so as to explore the influence of leading edge erosion on the flow characteristics of subsonic cascade in high altitude and low Reynolds number environment.The results showed that at 0°angle of attack,the low Reynolds number condition weakened the sensitivity of the airflow to the leading edge morphology,so that the pressure distribution at the leading edge,the flow separation and transition of the boundary layer on the suction surface,and the separation degree of the trailing edge of the three airfoils tended to be consistent.Finally,the increase of total pressure loss caused by the leading edge erosion became smaller with the decrease of Reynolds number,and the total pressure loss coefficient and pressure ratio of the three airfoils tended to be consistent.At the angle of attack of 4°,the leading edge erosion can promote the occurrence of transition at low Reynolds number and reduce the degree of trailing edge separation,so that the total pressure loss was less than 0°angle of attack;when the inlet Mach number was 0.6,it reduced by 23.6%,and when 0.8,it reduced by 41.2%.
作者
史磊
郑宇翔
方文博
郭姝含
熊杰
SHI Lei;ZHENG Yuxiang;FANG Wenbo;GUO Shuhan;XIONG Jie(Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China;Department of Aeronautics and Astronautics,University of Southampton,Southampton,SO171BJ,United Kingdom)
出处
《航空动力学报》
北大核心
2025年第12期299-313,共15页
Journal of Aerospace Power
基金
中央高校基本科研业务费中国民航大学专项(3122024028)
民航航空器适航审定技术重点实验室开放基金(SH2022070501)。
关键词
低雷诺数
亚声叶型
前缘侵蚀
边界层
流动分离
转捩
low Reynolds number
subsonic cascade
leading edge erosion
boundary layer
flow separation
transition
