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Effects of slot jet and its improved approach in a high-load compressor cascade

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Abstract

Experimental investigations are conducted in this paper to study a slot jet approach. Measurements inside a high-load compressor cascade were performed to evaluate its gains and reveal its mechanisms. Further, an improved approach is developed on the basis of the individual slot jet approach. Experiments shows that the individual slot jet is highly efficient at reducing trailing-edge separation by directly speeding up separated fluids, but it is not so efficient at reducing the corner stall. To further reduce the corner stall, the improved approach introduces a vortex generator into the flow field. The individual slot jet partly reduces corner stall by restricting the passage vortex and concentrating the separation at the cascade corner, which happens to offer convenient conditions for the vortex generator to further reduce flow loss. The vortex generator, which produces a counter-rotating vortex to counteract the passage vortex, prevents the formation of the end-wall cross flow. Therefore, both the trailing-edge separation and corner stall are significantly suppressed, so that the improved approach achieves more powerful flow control effects.

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References

  • Akcayoz E, Vo HD, Mahallati A (2015) Controlling corner stall separation with plasma actuators in a compressor cascade. ASME Paper No. 2015-43404. doi:10.1115/1.4032675

  • Bernardini C, Benton SI, Bons JP (2013) The effect of acoustic excitation on boundary layer separation of a highly loaded LPT blade. J Turbomachinery 135(5):051001. doi:10.1115/1.4007834

    Article  Google Scholar 

  • Brent JA, Jones BA, Rockenbach RW (1970) Single stage experimental evaluation of compressor blading with slots and vortex generators. Part 1—analysis and design of stages 4 and 5. NASA-CR-72626

  • Cao C, Wang R, Zhou M, Wang Q (2007) Numerical simulation on cascade characteristics with slot from pressure surface to suction surface. J Aerospace Power 22(5):814–817

    Google Scholar 

  • Chu W, Li X, Wu Y, Zhang H (2016) Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall: a new design approach based on end wall velocity modification. Aerospace Sci Technol 55:76–91. doi:10.1016/j.ast.2016.05.011

    Article  Google Scholar 

  • Guo S, Lu H, Chen F, Wu C (2013) Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction. Exp Fluids 54(7):1–11. doi:10.1007/s00348-013-1570-y

    Article  Google Scholar 

  • Hecklau M, Wiederhold O, Zander V, King R, Nitsche W et al (2013) Active separation control with pulsed jets in a critically loaded compressor cascade. AIAA J 49(8):1729–1739. doi:10.2514/1.J050931

    Article  Google Scholar 

  • Hergt A, Meyer R, Engel K (2006) Experimental investigation of flow control in compressor cascades. ASME Paper No. 2006-90415. doi:10.1115/GT2006-90415

  • Hergt A, Meyer R, Engel K (2013) Effects of vortex generator application on the performance of a compressor cascade. J Turbomachinery 135(2):021026. doi:10.1115/1.4006605

    Article  Google Scholar 

  • Hu J, Wang R, Wu P, He C (2016a) Separation control by slot jet in a critically-loaded compressor cascade. Int J Turbo Jet Engines. doi:10.1515/tjj-2016-0044

    Google Scholar 

  • Hu J, Wang R, Li R, He C, Li Q (2016b) Experimental investigation on separation control by slot jet in highly loaded compressor cascade. Proc Inst Mech Eng Part G J Aerospace Eng. doi:10.1177/0954410017703145

    Google Scholar 

  • Kang S (1993) Investigation on the three dimensional flow within a compressor cascade with and without tip clearance. Ph.D. thesis, Vrije University Brussels, Brussels

  • Li YH, Wu Y, Zhou M, Su CB, Zhang XW, Zhu JQ (2010) Control of the corner separation in a compressor cascade by steady and unsteady plasma aerodynamic actuation. Exp Fluids 48(6):1015–1023. doi:10.1007/s00348-009-0787-2

    Article  Google Scholar 

  • Liu Y, Sun J, Tang Y, Lu L (2016) Effect of slot at blade root on compressor cascade performance under different aerodynamic parameters. Appl Sci 6(12):421. doi:10.3390/app6120421

    Article  Google Scholar 

  • MacMartin DG, Tillman TG (2000) Flow control opportunities in gas turbine engines. AIAA 2000-2234

  • Matejka M, Popelka L, Safarik P, Nozicka J (2008) Influence of active methods of flow control on compressor blade cascade flow. ASME Paper No. GT2008-51109. doi:10.1115/GT2008-51109

  • Ramzi M, AbdErrahmane G (2013) Passive control via slotted blading in a compressor cascade at stall condition. J Appl Fluid Mech 6(4):571–580

    Google Scholar 

  • Ramzi M, Bois G, Abderrahmane G (2011) Numerical study of passive control with slotted blading in highly loaded compressor cascade at low Mach number. Int J Fluid Mach Syst 4(1):97–103. doi:10.5293/IJFMS.2011.4.1.097

    Article  Google Scholar 

  • Wu P, Wang R, Guo F, Hu J, Li K (2016) Mechanism analysis of effects of vortex generator on high-load compressor cascade. J Propuls Technol 37(1):49–56. doi:10.13675/j.cnki.tjjs.2016.01.007

    Google Scholar 

  • Zhang X, Zhou M, Wang R, Xu X (2006) Research on the effect of jet flow from pressure surface to suction surface on performance of blade. Acta Aerodynamica Sinica 24(2):152–156

    Google Scholar 

  • Zhang H, Wang S, Wang Z (2007) Variation of vortex structure in a compressor cascade at different incidences. J Propuls Power 23(1):221–226. doi:10.2514/1.17245

    Article  Google Scholar 

  • Zhao GJ, Fu C, Song YP, Wang ZQ (2004) Experimental study on the aerodynamic performance of swept curved blade. Chin J Aeronaut 17(3):136–141

    Article  Google Scholar 

  • Zhong J, Han J A, Liu Y, Tian F (2008) Numerical simulation of endwall fence on the secondary flow in compressor cascade. ASME Paper No. 2008-50888. doi:10.1115/GT2008-50888

  • Zhou M, Wang R, Zeng L, Zhao Y (2008) Effect of slot width on the aerodynamic performance of compressor cascade. J Aerospace Power 23(6):1077–1081

    Google Scholar 

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Acknowledgements

This work was supported by the National Natural Science Foundation of China (No. 51336011). All of the authors participated in the research and commented on the final manuscript.

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Authors and Affiliations

  1. School of Aeronautics and Astronautics Engineering, Air Force Engineering University, 1 Balin Road, Baqiao District, Xi’an, 710038, China

    Jiaguo Hu, Rugen Wang, Renkang Li & Peigen Wu

  2. School of Energy and Power Engineering, Beihang University, 37 Xueyuan Road, Haidian District, Beijing, 100191, China

    Jiaguo Hu

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  1. Jiaguo Hu
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  2. Rugen Wang
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  3. Renkang Li
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  4. Peigen Wu
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Correspondence to Jiaguo Hu.

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Hu, J., Wang, R., Li, R. et al. Effects of slot jet and its improved approach in a high-load compressor cascade. Exp Fluids 58, 155 (2017). https://doi.org/10.1007/s00348-017-2437-4

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