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Journal of Thermal Science

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2022 , Vol. 31 >Issue 5: 1804 - 1819

DOI: https://doi.org/10.1007/s11630-022-1657-y

气动

Comparison of Flow Mechanism of Blade Sweep between a Transonic Single Rotor and a Rotor in Stage Environment

  • CAO Zhiyuan ,
  • GAO Xi ,
  • LIANG Yuyuan ,
  • HUANG Ping ,
  • LEI Peng ,
  • LIU Bo
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  • 1. School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
    2. AECC Sichuan Gas Turbine Research Establishment, Chengdu 610599, China

网络出版日期: 2023-12-01

基金资助

The authors would like to acknowledge the supports of National Natural Science Foundation of China (No. 51806174), National Science and Technology Major Project (J2019-II-0011-0031), and National Natural Science Foundation of China (No. 51790512). Thanks for the funding from AECC Sichuan Gas Turbine Research Establishment. Thanks for the help of Prof. Nie Chaoqun from Institute of Engineering Thermophysics, Chinese Academy of Sciences during the flow mechanism analysis.

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
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Comparison of Flow Mechanism of Blade Sweep between a Transonic Single Rotor and a Rotor in Stage Environment

  • CAO Zhiyuan ,
  • GAO Xi ,
  • LIANG Yuyuan ,
  • HUANG Ping ,
  • LEI Peng ,
  • LIU Bo
Expand
  • 1. School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
    2. AECC Sichuan Gas Turbine Research Establishment, Chengdu 610599, China

Online published: 2023-12-01

Supported by

The authors would like to acknowledge the supports of National Natural Science Foundation of China (No. 51806174), National Science and Technology Major Project (J2019-II-0011-0031), and National Natural Science Foundation of China (No. 51790512). Thanks for the funding from AECC Sichuan Gas Turbine Research Establishment. Thanks for the help of Prof. Nie Chaoqun from Institute of Engineering Thermophysics, Chinese Academy of Sciences during the flow mechanism analysis.

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
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摘要

为了揭示叶片掠形在单转子和级环境下对风扇气动性能的不同影响机理，本文针对两级风扇NASA CR-120859的第一级风扇进行了掠形设计与数值模拟研究。结果表明，叶片掠形对单转子和级环境下风扇的气动性能影响不同，表明单转子条件下的掠形设计可能无法适用于级环境条件。叶片掠形对性能的不同影响是由于单转子和级环境下风扇的流场特性和失速机理的区别；风扇单转子的失速是激波/叶尖泄漏涡之间的干涉造成的，级环境下风扇的失速是轮毂区严重的角区分离造成的。对于风扇单转子，所有的前掠方案均可增加稳定裕度，而后掠总体上降低了稳定裕度。在级环境下，后掠转子显著增加了稳定裕度，失速机理转变为激波/泄漏涡干涉，前掠可减小稳定裕度。叶片掠形对风扇流场的影响机理是前掠减小了叶尖区域靠近前缘的叶片负荷，同时引起激波向下游移动，这两种变化均改善了叶尖区域的流场，而后掠的作用则相反；在轮毂区域，后掠通过改变径向压力梯度减小了径向流动趋势，从而减小了角区分离，而前掠则加剧了角区分离。随着掠高和掠角的增大，对于风扇单转子和级环境，前掠的堵塞流量、峰值效率和总压比总体上降低，后掠则相反。

关键词： sweep; tip leakage flow; shock; corner separation; transonic fan

本文引用格式

CAO Zhiyuan , GAO Xi , LIANG Yuyuan , HUANG Ping , LEI Peng , LIU Bo . Comparison of Flow Mechanism of Blade Sweep between a Transonic Single Rotor and a Rotor in Stage Environment[J]. 热科学学报, 2022 , 31(5) : 1804 -1819 . DOI: 10.1007/s11630-022-1657-y

Abstract

In order to reveal the different effect mechanisms of blade sweep on the aerodynamic performance when a transonic rotor operates alone or in fan stage environment, two series of forward and backward swept rotors were designed and utilized in the first stage of the dual-stage NASA CR-120859 fan. Results show that, the influence of sweep on the single rotor and the whole stage is different, indicating swept designs for rotor alone may not be suitable for the stage operations. The distinct effect of sweep is account for the difference of the flow field characteristic and stall mechanism of the single rotor and the rotor in the stage environment. The single rotor is tip limited and its stall mechanism is shock/tip leakage vortex (TLV) interaction, whereas the fan stage is hub limited and its stall mechanism is the severe corner separation at stage hub region. For the single rotor, forward sweep increases the stall margin (SM) for all sweep schemes, while backward sweep reduces it in general. For the fan stage, however, backward swept rotor significantly increases stall margin and the stall mechanism is changed to shock/TLV interaction. On the contrary, forward sweep reduces stall margin in general. The flow mechanism is that forward sweep reduces blade loading at tip region near leading edge (LE) and causes the shock to move downstream. Both the variations improve flow field at tip region, while backward sweep exerts an opposite effect. At hub region, backward sweep reduces radial flow tendency by varying radial pressure gradient, causing reduction of corner separation at rotor hub, while forward sweep enhances corner separation. Moreover, with increasing of swept height and swept angle, the chock mass flow, peak efficiency and total pressure ratio of forward sweep are reduced in general, while an opposite effect can be found for backward sweep.

Key words： sweep; tip leakage flow; shock; corner separation; transonic fan

参考文献

[1] Day I.J., Stall inception in axial flow compressors. Journal of Turbomachinery, 1993, 115(1): 1–9.
[2] Tang Y.M., Liu Y.W., Lu L.P., Evaluation of compressor blading with blade end slots and full-span slots in a highly loaded compressor cascade. Journal of Turbomachinery, 2019, 141(12): 121002.
[3] Sun S.J., Wang S., Chen S., The influence of diversified forward sweep heights on operating range and performance of an ultra-high-load low-reaction transonic compressor rotor. Energy, 2020, 194: 116857.
[4] Tang Y.M., Liu Y.W., Lu L.P., Lu H.W., Wang M., Passive separation control with blade-end slots in a highly loaded compressor cascade. AIAA Journal, 2020, 58(1): 85–97.
[5] Mohankumar B., Hall C.A., Wilson M.J., Sweep effects on fan-intake aerodynamics at high angle of attack. Journal of Turbomachinery, 2022, 144(10): 101001.
[6] Lei F., Ju Y.P., Zhang C.H., A rapid and automatic optimal design method for six-stage axial-flow industry compressor. Journal of Thermal Science, 2021, 30(5): 1658–1673.
[7] Pan T.Y., Wu W.Q., Zheng M.Z., Li Q.S., Instability inception of a single rotor embedded in a transonic stage with partial surge inception. Journal of Thermal Science, 2022, 31(1): 130–140.
[8] Gümmer V., Wenger U., Kau H.P., Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors. Journal of Turbomachinery, 2001, 123(1): 40–48.
[9] Govardhan M., Kumar O.G.K., Sitaram N., Computational study of the effect of sweep on the performance and flow field in an axial flow compressor rotor. Proceedings of the iMeche, Part A: Journal of Power and Energy, 2007, 221(3): 315–329.
[10] Ramakrishna P.V., Govardhan M., On loading corrections and loss distributions in low-speed forward swept axial compressor rotors. Proceedings of the iMeche, Part A: Journal of Power and Energy, 2011, 225(1): 120–130.
[11] Ilikan A.N., Ayder E., Influence of the sweep stacking on the performance of an axial fan. Journal of Turbomachinery, 2015, 137(6): 061004.
[12] Benini E., Biollo R., Aerodynamics of swept and leaned transonic compressor-rotors. Applied Energy, 2007, 84(10): 1012–1027.
[13] Denton J.D., Xu L.P., The effects of lean and sweep on transonic fan performance. ASME Paper, 2002, No. GT-2002-30327.
[14] Hah C., Wennerstrom A.J., Three-dimensional flow fields inside a transonic compressor with swept blades. Journal of Turbomachinery, 1991, 113(2): 241–250.
[15] Cui W.W., Xiang X.R., Zhao Q.J., Xu J.Z., The effect of sweep on flow fields of a highly loaded transonic rotor. Aerospace Science and Technology, 2016, 58: 71–81.
[16] He C., Ma Y., Liu X., Sun D. Sun X., Aerodynamic instabilities of swept airfoil design in transonic axial-flow compressors. AIAA Journal, 2018, 56(5): 1878–1893.
[17] He C., Sun D., Sun X., Stall inception analysis of transonic compressors with chordwise and axial sweep. Journal of Turbomachinery, 2018, 140(4): 041009.
[18] Wadia A.R., Niedermeier J.D., Szucs P.N., Cormier N.G., Crall D.W., Rabe D.C., Aerodynamic design and testing of an imbedded forward swept rotor in a two-stage transonic fan. Journal of Turbomachinery, 2019, 141(8): 081012.
[19] McNulty G.S., Decker J.J., Beacher B.F., Khalid S.A., The impact of forward swept rotors on tip clearance flows in subsonic axial compressors. Journal of Turbomachinery, 2004, 126(4): 445–454.
[20] Sun S.J., Wang S., Chen S., Tao C., Cai L., Chen J.W., The impact of various forward sweep angles on the performance of an ultra-high-load low-reaction transonic compressor rotor. Applied Thermal Engineering, 2019, 150: 953–966.
[21] Okui H., Verstraete T., Braembussche R.A., Alsalihi Z., Three-dimensional design and optimization of a transonic rotor in axial flow compressors. Journal of Turbomachinery, 2013, 135(3): 031009.
[22] Huang S., Zhou C.X., Yang C.W., Zhao S., Lu X., Effect of backward sweep on aerodynamic performance of a 1.5-stage highly loaded axial compressor. ASME Paper, 2020, No. GT2020-14262.
[23] Messenger H.E., Kennedy E.E., Two-stage fan I: aerodynamic and mechanic design. NASA Report, 1972, No. CR-120859.
[24] Wu Y.H., Li Q.P., Tian J.T., Chu W.L., Investigation of pre-stall behavior in an axial compressor rotor—part II: flow mechanism of spike emergence. Journal of Turbomachinery, 2012, 134(5): 051028.
[25] Sakuma Y., Watanabe T., Himeno T., Kato D., Murooka T., Shuto Y., Numerical analysis of flow in a transonic compressor with a single circumferential casing groove: influence of groove location and depth on flow instability. Journal of Turbomachinery, 2014, 136(3): 031017.
[26] Zheng X.Q., Sun Z.Z., Kawakubo T., Tamaki H., Stability improvement of a turbocharger centrifugal compressor by a non-axisymmetric vaned diffuser. Journal of Turbomachinery, 2018, 140(4): 041007.
[27] Liu X.H., Teng J.F., Calculation of stall margin enhancement with micro tip injection in an axial compressor. Journal of Fluids Engineering, 2019, 141(8): 081109.
[28] Strazisar A.J., Wood J.R., Hathaway M.D., Suder K.L., Laser anemometer measurements in a transonic axial flow fan rotor. NASA Report, 1989, No. 2879.
[29] Liu Y.W., Yu X.J., Liu B.J., Turbulence models assessment for large-scale tip vortices in an axial compressor rotor. AIAA Journal of Propulsion and Power, 2008, 24(1): 15–25.
[30] Mailach R., Lehmann I., Vogeler K., Periodical unsteady flow within a rotor blade row of an axial compressor—part II: wake-tip clearance vortex interaction. Journal of Turbomachinery, 2008, 130(4): 041005.
[31] Du J., Lin F., Chen J., Nie C.Q., Biela C., Flow structures in the tip region for a transonic compressor rotor. Journal of Turbomachinery, 2013, 135(3): 031012.
[32] Biollo R., Benini E., Shock/boundary-layer/tip-clearance interaction in a transonic rotor blade. Journal of Propulsion and Power, 2009, 25(3): 668–677.
[33] Wadia A.R., Szucs P.N., Crall D.W., Inner working of aerodynamic sweep. Journal of Turbomachinery, 1998, 120(4): 671–682.
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