非光滑表面叶片气动及降噪特性的研究  

Study on Noise Reduction Characteristics of Blade with Non-Smooth Surface

作　　者：刘家成 陈二云[1] 杨爱玲[2] 李国平[3] LIU Jia-cheng;CHEN Er-yun;YANG Ai-ling;LI Guo-ping(College of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai,China,Post Code:200093;Key Laboratory of Multiphase Flow and Heat Transfer of Power Engineering,University of Shanghai for Scienee and Technology,Shanghai,China,Post Code:200093;Shanghai Marine Equipment Research Institute,Shanghai,China,Post Code:200031)

机构地区：[1]上海理工大学能源与动力工程学院,上海200093 [2]上海理工大学上海市动力工程多相流动与传热重点实验室,上海200093 [3]上海船舶设备研究所,上海200031

出　　处：《热能动力工程》2020年第12期31-39,共9页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金(51106099,50976072)。

摘　　要：基于非光滑表面技术,研究了叶片表面凹坑结构对气动、绕流流场和噪声特性的影响。流场计算采用大涡模拟技术,声场采用LMS Virtual.lab直接边界元法。通过与Fluent FW-H积分法对比,证明采用直接边界元法的可靠性。结果表明:吸力面凹坑引起叶片气动性能轻微下降,大攻角下一定形状的坑面可以延迟壁面分离,实现减阻增升效果;叶片外部流场的雷诺数为2×105,叶片绕流边界层的涡流结构具有明显二维特征,凹坑曲面的存在限制了转捩过程中分离涡的展向发展,将大涡破碎成小涡;凹坑降低了叶片尾缘处压力脉动及气动噪声,相对位置和曲面形状均影响降噪效果,0°时改型模型的总声压级均有所下降,最大下降约为5 dB,占原来总声压级的10%。Based on the non-smooth surface technology, the effects of blade surface pit structure on aerodynamic, flow field and noise characteristics were studied. Large eddy simulation(LES) was used to calculate the flow field and LMS Virtual.lab Direct boundary element method(BEM) was used in the sound field. Compared with fluent FW-H integral method, the reliability of the direct boundary element method is proved. The results show that:the cavitation on the suction surface causes a slight decrease in the aerodynamic performance of the blade, and a certain shape of the pit can delay the wall separation at high angle of attack to achieve the effect of reducing drag and increasing lift.The Reynolds number of the external flow field of the blade is 2×10~5, and the vortex structure of the boundary layer around the blade has obvious two-dimensional characteristics, and the existence of the concave surface restricts the development of the separation vortex along the span direction in the transition process, which will cause the large vortex.The cavitation reduces the pressure fluctuation at the trailing edge of the blade and effectively reduces the aerodynamic noise. The relative position and the shape of the curved surface affect the noise reduction effect. The total sound pressure level of the modified model decreases at 0° and the maximum drop is about 5 dB, accounting for 10% of the original total sound pressure level.

关 键 词：非光滑表面 边界元积分 压力脉动 总声压级 

分 类 号：TK221[动力工程及工程热物理—动力机械及工程]