吸力面波系分布对风扇激波噪声的影响  

The Influence of Wave System on the Suction Surface on the Buzz-saw Noise of Turbofan

作　　者：葛健 柳阳威[1,2] 周振华 陆利蓬 孙晓峰[1,2] GE Jian;LIU Yang-Wei;ZHOU Zhen-Hua;LU Li-Peng;SUN Xiao-Feng(National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China;China Academy of Space Technology,Beijing 100076,China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191 [3]北京空间机电研究所,北京100076

出　　处：《工程热物理学报》2018年第11期2389-2397,共9页Journal of Engineering Thermophysics

基　　金：国家自然科学基金项目(No.51676007;No.51420105008;No.51790513)

摘　　要：数值探究了前缘和吸力面的形状对风扇激波噪声的影响,分析讨论了吸力面上膨胀波和压缩波与前伸激波的干涉对激波噪声的影响机理,提出了降低风扇激波噪声的前缘和吸力面改型方法,分别在一个二维超声叶型和一个三维跨声转子上进行实验。结果表明优化后的前缘和吸力面形状可有效减弱吸力峰的强度,消除气流在前缘附近的过膨胀和再压缩过程,改善吸力面的波系分布,可降低二维超声叶型的激波噪声约3 dB,降低三维跨声转子的激波噪声约1.5 dB。The influence of the shape of leading edge and suction surface of blade on the buzz-saw noise has studied and the effect of the interference between the expansion and compression wave and the bow shock has been discussed. Besides, a creative leading edge and suction surface optimization method has been raised to decrease the buzz-saw noise which has been experimented on a supersonic cascade and a transonic rotor. The results show that the optimized blades can reduce the strength of spike on the suction side, and eliminate the over-expansion and re-compression process leading to an improvement of wave system distribution. It shows that after the optimization, the buzz-saw noise of the cascade drops by about 3 dB, and the one of rotor declines by about 1.5 dB.

关 键 词：激波噪声 前缘 叶型优化 吸力峰 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]