Effects of dimples with different depths in a highly loaded compressor cascade

  • YANG Yi ,
  • LU Hua-wei ,
  • GUO Shuang ,
  • PANG Wen-xuan ,
  • WANG Yu ,
  • ZHONG Jing-jun
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  •  (1. Naval Architecture & Ocean Engineering College, Dalian Maritime University, Dalian 116026, China;2. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China)

Received date: 2018-05-03

  Revised date: 2018-05-25

  Online published: 2018-05-31

Supported by

 

Abstract

 Inspired by idea of “bionics”, this paper attempted to apply the nonsmooth shape of spherical dimples to the suction surface of a typical highly loaded compressor cascade to explore its influence on the flow characteristics of the cascade. Four rows dimples with depths of 0.2 mm~0.6 mm at the 38 %~60 % chord length on the suction side were selected as research object, and the Reynolds averaged method based on experimental verification was used for steady calculation. Results show that the array of dimples can effectively eliminate the separation bubble along the direction of blade spanning, and make the streamwise separation position of corner region move to the trailing edge of the blade at the same time. Under the designed Mach number, the dimple also inhibits the migration of passage vortex along the spanwise direction, simplifying the vortex structure in the corner zone. Based on the above reasons, the five kinds of dimples arranged upstream from the separation region can effectively reduce the total pressure loss at the exit of cascade, and the maximum loss reduction is up to 10.8 %. Additionally, the flow loss shows an increasing trend with the increase of dimple depth.

Cite this article

YANG Yi , LU Hua-wei , GUO Shuang , PANG Wen-xuan , WANG Yu , ZHONG Jing-jun . Effects of dimples with different depths in a highly loaded compressor cascade[J]. Journal of Dalian Maritime University, 2018 , 44(4) : 83 -91 . DOI: 10.16411/j.cnki.issn1006-7736.2018.04.013

References

[1] Cumpsty N A. Compressor Aerodynamics[M]. Longman Scientific & Technical, 1989.
[2] Shang Erbing, Wang Zhong-qi, Su Xian-jie. The experimental investigations on the compressor cascades with leaned and curved blade[C]. ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. ASME, 1993: V001T03A018-V001T03A018.
[3] GUO Shuang, LU Hua-wei, CHEN Fu, et al. Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction[J]. Experiments in Fluids, 2013, 54(7): 1570.
[4] ZHAO, Xiao-hu, LI, Ying-hong, WU Yun, et al. Numerical Investigation of Flow Separation Control on a Highly Loaded Compressor Cascade by Plasma Aerodynamic Actuation[J]. Chinese Journal of Aeronautics, 2012, 25(3): 349-360.
[5] Abdulbari H A, Mahammed H D, Hassan Z B Y. Bio-inspired passive drag reduction techniques: a review[J]. ChemBioEng Reviews, 2015, 2(3):185-203.
[6] Tian Li-mei, Li Zi-yuan, Jin E, et al. Improved flow performance of a centrifugal compressor based on pit formation on the notum of the whirligig beetle (Gyrinidae Latreille)[J]. Advances in Mechanical Engineering, 2015, 7(7):1687814015591736.
[7] Kwon H G, Sang D H, Cho H H. Measurement of local heat/mass transfer coefficients on a dimple using naphthalene sublimation[J]. International Journal of Heat & Mass Transfer, 2011, 54(5-6):1071-1080.
[8] Rao Yu, Li Bo, Feng Yan. Heat transfer of turbulent flow over surfaces with spherical dimples and teardrop dimples[J]. Experimental Thermal and Fluid Science, 2015, 61:201-209.
[9] Mahmood G I, Ligrani P M. Heat transfer in a dimpled channel: combined influences of aspect ratio, temperature ratio, Reynolds number, and flow structure[J]. International Journal of Heat and mass transfer, 2002, 45(10):2011-2020.
[10] Tay C M, Lim T T. Drag reduction with non-axisymmetric dimples[C]. 35th AIAA Applied Aerodynamics Conference. 2017: 2017-3569.
[11] Bearman P W, Harvey J K. Control of circular cylinder flow by the use of dimples[J]. AIAA Journal, 1993, 31(10):1753-1756.
[12] Bearman P W, Harvey J K. Golf ball aerodynamics[J]. The Aeronautical Quarterly, 1976, 27(2):112-122.
[13] Butt U, Jehring L, Egbers C. Mechanism of drag reduction for circular cylinders with patterned surface[J]. International Journal of heat and fluid Flow, 2014, 45:128-134.
[14] 赵军. 凹坑形仿生非光滑表面的减阻性能研究[D]. 大连理工大学, 2008.
Zhao Jun. Study of Drag Reduction Capability of the Dimple Bionic Non-smooth Surface[D]. Dalian University of Technology, 2008.
[15] Lake J, King P, Rivir R. Reduction of separation losses on a turbine blade with low Reynolds numbers[C]. 37th Aerospace Sciences Meeting and Exhibit. 1999: 242.
[16] Rivir R B, Sondergaard R, Bons J P, et al. Control of separation in turbine boundary layers[C]. 2nd AIAA Flow Control Conference. 2004: 2004-2201.
[17] Lan Ji-bing, Xie Yong-hui, Zhang Di. Effect of leading edge boundary layer thickness on dimple flow structure and separation control[J]. Journal of Mechanical Science and Technology, 2011, 25(1): 3243-3251.
[18] Casey J P, King P I, Sondergaard R. Parameterization of boundary layer control dimples on a low pressure turbine blade[C]. 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, VA, USA: AIAA. 2004, 2004-3570.
[19] 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,2013,28(4):893-902.
Yang Lin, Qiao Wei-yang, Mu Zhong-qiang, et al. Flow loss control of turbine based on “groove” and “dimple” technology with low Reynolds number[J]. Journal of Aerospace Power, 2013, 28(4): 893-902.
[20] Zhao Y, Lu H, Sun Y. Experimental studies of dimpled surface effect on the performance of linear cascade under different incidence angles[J]. Procedia CIRP, 2016, 56:137-142.
[21] Zhang Hai-deng, Wu Yun, Li Ying-hong, et al. Experimental investigation on a high subsonic compressor cascade flow. Chinese Journal of Aeronautics 2015 28(4): 1034-1043.
[22] Kang S.Investigation of the Three dimensional flow within a compressor cascade with and without Tip Clearance[D]. Brussel: Vrije Universiteit Brussel, 1993.
[23] Kang Shun, Wang Zhongqi. Application of topological analysis to studying the three-dimensional flow in cascades; part I. topological rules for skin-friction lines and section streamlines[J]. Applied Mathematics and Mechanics. 1990, 11(5): 489-495.
[24] Hunt J C R, Wray A A, Moin P. Eddies, Stream, and Convergence Zones in Turbulent Flows[R]. Report CTR-S88, Centre for Turbulence Research, 1988.
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