凹坑尺寸大小对二维扩压叶栅损失特性影响的数值研究

庞文瑄; 陆华伟; 宋洪达; 郭爽; 王宇; 杨帆

doi:10.16411/j.cnki.issn1006-7736.2019.02.011

大连海事大学学报 >

2019 , Vol. 45 >Issue 2: 77 - 84

DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2019.02.011

热能与动力

凹坑尺寸大小对二维扩压叶栅损失特性影响的数值研究

庞文瑄 ,
陆华伟 ,
宋洪达 ,
郭爽 ,
王宇 ,
杨帆

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（1.大连海事大学船舶与海洋工程学院，辽宁大连 116026；2.大连理工大学航空航天学院，辽宁大连 116024）

庞文瑄（1995 — ），男，硕士生，E-mail：wenxuan_pang@163.com.

收稿日期: 2018-10-13

修回日期: 2018-11-25

网络出版日期: 2018-11-25

基金资助

国家自然科学基金资助项目（51506022;51676023）;辽宁省自然科学基金资助项目（201602078）; 中央高校基本科研业务费专项资金资助项目（3132018203;DUT16K08）.

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Numerical investigation on the influence of dimple size on the loss performance of two-dimensional compressor cascade

PANG Wen-xuan ,
LU Hua-wei ,
SONG Hong-da ,
GUO Shuang ,
WANG Yu ,
YANG Fan

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(1.Naval Architecture and Marine Engineering College,Dalian Maritime University,Dalian 116026,China;2.School of Aeronautics and Astronautics,
Dalian University of Technology,Dalian 116024,China）

Received date: 2018-10-13

Revised date: 2018-11-25

Online published: 2018-11-25

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摘要

采用CFD数值模拟方法对某压气机静叶叶栅气动性能进行研究.在吸力面布置不同尺寸的凹坑，将深径比为0.25，球体半径分别为0.4、0.5、0.6、0.7 mm的凹坑布置在55% ~ 78%弦长位置，球状凹坑可以通过提高边界层内的湍动能水平使得附面层抵抗分离能力变强，从而抑制并延缓附面层分离，减小分离后的反流区域面积，有效减小矩形叶栅中径处的尾迹损失，改善流场.结果表明，球体半径为0.5 mm的凹坑效果较好，能够使叶栅出口总压损失降低17.63%.

关键词： 静叶叶栅; 凹坑尺寸; 损失特性; 数值研究

本文引用格式

庞文瑄 , 陆华伟 , 宋洪达 , 郭爽 , 王宇 , 杨帆 . 凹坑尺寸大小对二维扩压叶栅损失特性影响的数值研究[J]. 大连海事大学学报, 2019 , 45(2) : 77 -84 . DOI: 10.16411/j.cnki.issn1006-7736.2019.02.011

Abstract

CFD numerical simulation method was used to study the aerodynamic performance of a static cascade of a compressor. Different sizes of dimples were arranged on the suction surface, and the dimples with depth-diameter ratio of 0.25 and sphere radius of 0.4, 0.5, 0.6 and 0.7 mm were arranged at the chord length of 55%~78%.The spherical dimples can enhance the resistance of boundary layer to separation by increasing the turbulent kinetic energy level in the boundary layer, thus restraining and delaying the separation of boundary layer, reducing the area of the regurgitation region after separation, and effectively reducing the wake loss at the mid-diameter of rectangular cascade and improving the flow field. Results show that the dimple with a radius of 0.5 mm has a better effect, which can reduce the total pressure loss of the cascade outlet by 17.63%.

Key words： static cascade; dimple size; loss performance; separation

参考文献

[1]刘华坪, 张东飞, 陈焕龙.端壁射流对高速扩压叶栅性能的影响[J].工程热物理学报, 2017, 38(12):2569-2575
[2]GUO Shuang, LU Huawei, CHEN Fu, et al.Vortexcontrol and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction [J]. Experiments in Fluids, 2013, 54(7):
[3]Wallis R A.The Use of Air Jets for Boundary Layer Control[R]. Australia: Aerodynamics Research Laboratories, 1952.1570.
[4]ZHONG Jingjun, HAN Shaobing, LU Huawei, et al.Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade[J]. Chinese Journal of Aeronautics, 2013, 03:583-593.
[5]杨林，乔渭阳，母忠强，等.基于表面“凹槽”与“陷窝”技术的低雷诺数涡轮流动损失控制[J].航空动力学报，2013（04）893-902.
[6]ZHONGJingjun, HANShaobing, LUHuawei, et al.Effect of tip geometry and tip clearance on aerodynamic performance of a linear compressor cascade[J]. Chinese Journal of Aeronautics, 2013, 03:583-593.
[7]Reif W F.Morphogenesis and function of the squama-tion in sharks[J]. NeuesJahrbuch fur Geologie and Palaontolo-gie, Abhandlungen Band, 1982, 164:172-183.
[8]Bearman P W, Harvey J K.Control of circular cylinder flow by the use of dimples[J]. AIAA, J, 1993, 31:1753-1756.
[9]杨弘炜, 高歌.一种新型边界层控制技术应用于湍流减阻的实验研究[J].航空学报, 1997(04):72-74.
[10]Shclechtriem S，Lotzerich M.Breakdown of tip leak-age vorticesin compressors at flow conditions close to stall［R］.ASME paper97-GT-41，1997.
[11]Hah C，Rabe D C，Wadia A R.Role of tip-leakage vortices andpassage shock in stall inception in a swept transonic compressorrotor［R］. ASME Paper GT2004-53867，2004.
[12]禹世奇.压气机近失速状态流场非定常特性研究[D].南京航空航天大学, 2012.
[13]吴艳辉, 楚武利, 张皓光.轴流压气机失速初始扰动的研究进展, 力学进展, 2008, 38(5):571~584.
[14]陆华伟, 杨益, 郭爽, 黄宇轩, 钟兢军.不同位置凹坑控制高负荷扩压叶栅流动分离的数值研究[A].中国航天第三专业信息网第三十八届技术交流会暨第二届空天动力联合会议论文集——发动机内流气动技术[C].2017:10.
[15]LAN Jibing, XIE Yonghuiand ZHANG Di.Effectof leading edge boundary layer thickness on dimple flow structure and separation control[J].Journal of Mechani-cal Science and Technology, 2011, 25(1):3243-3251
[16]庞文瑄, 陆华伟, 郭爽, 王宇, 杨帆.凹坑位置影响二维扩压叶栅损失特性的数值研究[A].国工程热物理学会学术会议流体机械学术会议论文集. 西安, 2018.10

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