摘要
采用经实验校核的CFD方法研究吸力面不同深度的凹坑对高负荷扩压叶栅气动性能的影响。为研究不同凹坑方案对于叶栅损失特性的影响,深度为0.2、0.3、0.4、0.5、0.6mm,深宽比为0.25的5种凹坑分别被布置在42%~60%轴向弦长处。不同深度凹坑对于减小损失的效果不同。结果表明:深度为0.2mm的凹坑能够使得叶栅出口总压损失降低10.8%。三维球状凹坑通过提高边界层内的湍动能水平,促进边界层转捩,消除了层流分离泡,改善了矩形叶栅的气动性能。
The CFD investigation was verified by an experiment to study the aerodynamic performance of a highly-loaded compressor cascade with dimples of different depth.Five dimple configurations with diameters of 0.2,0.3,0.4,0.5,0.6 mm and a depth-diameter ratio of 0.25,were arranged in 42%-60% axial chord lengths of suction side respectively,and studied to validate their effectiveness in reducing total pressure loss.The dimples with different depth exhibited different performance in loss reduction.Result showed that,a10.8%loss reduction can be required under the influence of dimples whose depth was 0.2 mm.Three-dimensional spherical dimples can promote the transition of the boundary layer by enhancing the turbulent kinetic energy level.Given the eradication of the laminar separation bubble on the suction side,an improved aerodynamic performance of linear cascade can be required.
作者
陆华伟
杨益
郭爽
黄宇轩
钟兢军
LU Huawei;YANG Yi;GUO Shuang;HUANG Yuxuan;ZHONG Jingjun(School of Naval Architecture and Ocean Engineering,Dalian Maritime University,Dalian Liaoning 116026,China;School of Aeronautics and Astronautics,Dalian University of Technology,Dalian Liaoning 116024,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2018年第8期1933-1940,共8页
Journal of Aerospace Power
基金
国家自然科学基金(51676023
51506022
51436002)
辽宁省自然科学基金(201602078)
中央高校基本科研业务费专项资金(3132018203
DUT16K08)
关键词
高负荷扩压叶栅
凹坑
损失特性
转捩
分离
highly-loaded compressor cascade
dimple
loss performance
transition
separation
