低雷诺数下粗糙度对高亚声速压气机叶型气动性能的影响  

Effects of Surface Roughness on Aerodynamic Performance of a High Subsonic Compressor Airfoil under Low Reynolds Number Conditions

作　　者：王名扬 李紫良 卢新根[1,2] 赵胜丰 张燕峰[1,2] 朱俊强 WANG Ming-yang;LI Zi-liang;LU Xin-gen;ZHAO Sheng-feng;ZHANG Yan-feng;ZHU Jun-qiang(Key Laboratory of Light-Duty Gas-Turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院工程热物理研究所,轻型动力重点实验室,北京100190 [2]中国科学院大学,北京100049

出　　处：《推进技术》2020年第7期1510-1519,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(51836008);中国科学院前沿科学重点研究计划项目(QYZDB-SSW-JSC038)。

摘　　要：为了探究低雷诺数Re下粗糙度Ra对一高亚声速压气机叶型气动性能的影响,在其吸力面布置三种粗糙度分布,每种分布对应15种粗糙度大小。在Re=1.5×10^5时,利用数值模拟手段详细对比了不同粗糙度分布及大小下压气机叶片吸力面边界层分离、转捩规律,揭示了低Re下粗糙度调控压气机叶型边界层发展特性的机理。研究表明,三种粗糙度分布下,叶型损失随粗糙度大小的变化趋势类似。在转捩粗糙区,吸力面分离泡"位移效应"对叶型性能的不利影响随粗糙度增大而被抑制乃至完全消除,Ra=157μm时叶型损失最大分别降低10.16%,16.4%,15.58%;在完全粗糙区,随粗糙度进一步增大,强烈的湍流耗散作用反而致使叶型性能不断下降。在整个粗糙度大小范围内,粗糙度布置在吸力面前缘到转捩点之间时对边界层调控效果较好,能够较大限度地提升低Re下压气机叶型的气动性能。In order to investigate the effects of surface roughness Ra on the aerodynamic performance of a high subsonic compressor airfoil under low Reynolds number Re conditions,three roughness locations and fifteen roughness magnitudes were applied on the suction surface,respectively.At the Reynolds number of 1.5×10^5,the boundary layer separation and transition on the suction surface covered with different roughness locations and magnitudes were compared in detail,then the underlying physics of boundary layer development of compressor airfoil affected by roughness under low Reynolds number conditions were detected.Results showed that the trends of profile loss varied with the roughness magnitudes were similar to each other for the three roughness locations.In the transitionally rough region,the negative displacement effect of laminar separation bubble(LSB)over the suction surface on the airfoil performance was suppressed or even eliminated by the increased roughness magnitude,and the maximum reduction in profile loss were approximately 10.16%,16.4%and 15.58%for the three roughness locations,respectively,at Ra=157μm.On the other hand,with the further increase of roughness magnitude in the fully rough region,the airfoil performance was degraded gradually by the strong turbulent dissipation instead.Within the entire region of roughness magnitudes,the roughness covering from leading edge to the transition point on the suction surface has the potential to effectively control the boundary layer development,and the aerodynamic performance of compressor airfoil operating at low Re conditions was improved more distinctly.

关 键 词：低雷诺数 压气机 叶型 粗糙度 边界层 叶型损失 气动性能 

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]