Aeronautics and Astronautics

Effect of Moving Endwall on Hub Leakage Flow of Cantilevered Stator in a Linear Compressor Cascade

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  • (School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China)

Received date: 2021-02-19

  Online published: 2022-10-13

Abstract

The cantilevered stator has the advantages of reducing mass and axial length of highly loaded compressor. The details of the hub leakage flow resulting from the clearance between the high-speed moving hub and the cantilevered stator hub are unclear. In this paper, the effect of a moving endwall on the hub leakage flow of a cantilevered stator in a linear compressor cascade was studied. After the simulation method was verified with the experimental results, the time-averaged results of unsteady Reynolds averaged Navier-Stokes (URANS) were selected to study a case with a hub clearance of 2 mm. The results show that the effect of the moving endwall of the cantilevered cascade on the general characteristics with below 30% span increases the leakage mass flow rate and reduces the static pressure coefficient at three conditions of 0°, 6°, and -7° incidences, and the change is most significant at -7° incidence. The effect of the moving endwall on the total pressure loss coefficient varies with different operating conditions, which decreases by 15.94% at 0° incidence, and increases by 4.77% and 18.51% at 6° incidence and -7° incidence, respectively. The influence of the moving endwall is below 14% span at -7° incidence, below 23% span at 0° incidence, and below 30% span at 6° incidence. These effects correspond to the static pressure coefficient and the difference of static pressure coefficient representing the blade loading. In designing the cantilevered stator and matching between the stages of a multistage compressor, the quantitative research results of this paper have certain guiding significance.

Cite this article

ZHENG Biaojie (郑标颉), MA Yuchen (马宇晨), TENG Jinfang∗ (滕金芳), JU Zhenzhou (居振州), ZHU Mingmin (朱铭敏) . Effect of Moving Endwall on Hub Leakage Flow of Cantilevered Stator in a Linear Compressor Cascade[J]. Journal of Shanghai Jiaotong University(Science), 2022 , 27(6) : 780 -789 . DOI: 10.1007/s12204-022-2468-8

References

[1] JU Z Z, TENG J F, ZHU M M, et al. Flow characteristics on a 4-stage low-speed research compressor with a cantilevered stator [J]. Aerospace Science and Technology, 2020, 105: 106033. [2] DOUKELIS A, MATHIOUDAKIS K, PAPAILIOU K. The effect of tip clearance gap size and wall rotation on the performance of a high-speed annular compressor cascade [C]//ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. Stockholm, Sweden: ASME, 38. [3] DOUKELIS A, MATHIOUDAKIS K, PAPAILIOU K. Investigation of the 3-D flow structure in a high-speed annular compressor cascade for tip clearance effects [C]//ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. Stockholm, Sweden: ASME, 2014: 39. [4] WANG Y, MUTHANNA C, DEVENPORT W. The design and operation of a moving end-wall system for a compressor cascade wind tunnel [C]//37th Aerospace Sciences Meeting and Exhibit. Reno, NV, USA: AIAA, 1999: 741. [5] MUTHANNA C, DEVENPORT W J. Wake of a compressor cascade with tip gap, part 1: Mean flow and turbulence structure [J]. AIAA Journal, 2004, 42(11): 2320-2331. [6] WANG Y, DEVENPORT W J. Wake of a compressor cascade with tip gap, part 2: Effects of endwall motion [J]. AIAA Journal, 2004, 42(11): 2332-2340. [7] WENGER C W, DEVENPORT W J, WITTMER K S, et al. Wake of a compressor cascade with tip gap, part 3: Two point statistics [J]. AIAA Journal, 2004, 42(11): 2341-2346. [8] TIAN Q, SIMPSON R. Experimental study of tip leakage flow in the linear compressor cascade: Part I-stationary wall [C]//45th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, USA: AIAA, 2007: 269. [9] TIAN Q, SIMPSON R. Experimental study of tip leakage flow in the linear compressor cascade: Part II-effect of moving wall [C]//45th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, USA: AIAA, 2007: 270. [10] JIA X C, WANG Z M, CAI R X. Numerical investigation of different tip gap shape effects on aerodynamic performance of an axial-flow compressor stator [C]//ASME Turbo Expo 2001 : Power for Land, Sea, and Air. New Orleans, LA, USA: ASME, 2001: 337. [11] WU Y H, CHU W L. Influence of moving end-wall on tip clearance flow in axial compressor cascades [C]//44th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, USA: AIAA, 2006: 630. [12] PALLOT G, KATO D, KODAMA H, et al. The effect of the casing movement relative to the blades on the tip leakage loss in axial flow compressors [C]//ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. Vancouver, BC, Canada: ASME, 2012: 275-284. [13] KATO H, TANIGUCHI H, MATSUDA K, et al. Experimental and numerical investigation on compressor cascade flows with tip clearance at a low Reynolds number condition [J]. Journal of Thermal Science, 2011, 20(6): 481-485. [14] WILLIAMS R, GREGORY-SMITH D, HE L. A study of large tip clearance flows in an axial compressor blade row [C]//ASME Turbo Expo 2006 : Power for Land, Sea, and Air. Barcelona, Spain: ASME, 2008: 251-259. [15] SI X Y, TENG J F, QIANG X Q, et al. Different effects of cantilevered and shrouded stators on axial compressor performance [C]//ASME Turbo Expo 2017 : Turbomachinery Technical Conference and Exposition. Charlotte, NC, USA: ASME, 2017: 63261. [16] DU J, LIN F, CHEN J Y, et al. Flow structures in the tip region for a transonic compressor rotor [J]. Journal of Turbomachinery, 2013, 135(3): 031012. [17] MONTOMOLI F, NAYLOR E, HODSON H P, et al. Unsteady effects in axial compressors: A multistage simulation [J]. Journal of Propulsion and Power, 2013, 29(5): 1001-1008. [18] MAO X C, LIU B, ZHANG B T. Hub clearance effects of a cantilevered tandem stator on the performance and flow behaviors in a small-scale axial flow compressor [J]. Aerospace Science and Technology, 2019, 91: 219-230. [19] YU X J, ZHANG Z B, LIU B J. The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage [J]. Experimental Thermal and Fluid Science, 2013, 44: 301-311. [20] WANG S T, DU X, WANG Z Q. Study on the effects of end-bend cantilevered stator in a 2-stage axial compressor [J]. Journal of Thermal Science, 2009, 18(2): 119-125. [21] LUO J, HU J, WANG Z Q, et al. Experimental study of effects of bowed blade on the flow field in a cantilevered stator passage [C]//ASME Turbo Expo 2014 : Turbine Technical Conference and Exposition. Düsseldorf, Germany: ASME, 2014: 25766.
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