Volume 41 Issue 6
Jun.  2026
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2026  >  41(6): 20240657
SUN Shuxian, WANG Liang, WEI Gang, et al. Application of compressibility corrected γ-Reθt transition model in turbomachinery[J]. Journal of Aerospace Power, 2026, 41（6）：20240657 doi: 10.13224/j.cnki.jasp.20240657
Citation: SUN Shuxian, WANG Liang, WEI Gang, et al. Application of compressibility corrected γ-Reθt transition model in turbomachinery[J]. Journal of Aerospace Power, 2026, 41（6）：20240657 doi: 10.13224/j.cnki.jasp.20240657
shu

Application of compressibility corrected γ-Reθt transition model in turbomachinery

doi: 10.13224/j.cnki.jasp.20240657
  • 1.

    School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

  • 2.

    National Research Institute for Rural Electrification，Ministry of Water Resources，Development Research Center of Rural Water and Hydropower，Hangzhou 310012，China

  • 3.

    Aero Engine Corporation of China，Beijing 101304，China

  • 4.

    Institute for Aero Engine，Tsinghua University，Beijing 100084，China

  • Received Date: 2024-09-23
    Available Online: 2026-03-30
    Abstract

  • Two compressibility corrected methods developed from the original γ-Reθt transition model were applied to predict the boundary layer transition in the internal flow of turbomachinery. Considering the Mach number and temperature, the first method corrected the functional relationship between the vorticity Reynolds number (Rev) and the momentum thickness Reynolds number (Reθ) in the boundary layer. Subsequently, it employed the compressible Reynolds number analogy relation fRe to correct the original incompressible transition correlation function. The second method accounted for the influence of high-Mach number effects on the pressure gradient parameter and the variability of turbulent Prandtl number in real flow, and corrected these two parameters accordingly. The two corrected methods were implemented on our team's in-house solver, and transition predictions were conducted using three typical turbomachinery cases, followed by a comparative analysis with the original transition model. The results indicated that in the internal flow of turbomachinery, the first correction method showed a significant improvement, while the second one exhibited little difference from the original model. However, when dealing with the boundary layer transition induced by flow separation, both methods yielded predictions that were nearly identical to those of the original model.

     

    • FullText(HTML)
  • loading
    • References(21)
  • [1]
    杨琳, 邹正平, 宁方飞, 等. 边界层转捩的数值模拟[J]. 航空动力学报, 2005, 20(3): 355-360. YANG Lin, ZOU Zhengping, NING Fangfei, et al. Simulation of boundary layer transition[J]. Journal of Aerospace Power, 2005, 20(3): 355-360. (in Chinese doi: 10.19596/j.cnki.1001-246x.8600

    YANG Lin, ZOU Zhengping, NING Fangfei, et al. Simulation of boundary layer transition[J]. Journal of Aerospace Power, 2005, 20(3): 355-360. (in Chinese) doi: 10.19596/j.cnki.1001-246x.8600
    [2]
    王文涛, 王子楠, 张宏武, 等. 压气机静叶栅层流分离泡转捩与角区分离数值模拟与实验[J]. 航空动力学报, 2017, 32(9): 2273-2282. WANG Wentao, WANG Zinan, ZHANG Hongwu, et al. Numerical simulation and experiment of laminar separation bubble transition and corner separation of compressor stator cascade[J]. Journal of Aerospace Power, 2017, 32(9): 2273-2282. (in Chinese doi: 10.13224/j.cnki.jasp.2017.09.028

    WANG Wentao, WANG Zinan, ZHANG Hongwu, et al. Numerical simulation and experiment of laminar separation bubble transition and corner separation of compressor stator cascade[J]. Journal of Aerospace Power, 2017, 32(9): 2273-2282. (in Chinese) doi: 10.13224/j.cnki.jasp.2017.09.028
    [3]
    CHOI H, MOIN P. Grid-point requirements for large eddy simulation: Chapman’s estimates revisited[J]. Physics of Fluids, 2012, 24: 011702. doi: 10.1063/1.3676783
    [4]
    WALKER G J. The role of laminar-turbulent transition in gas turbine engines: a discussion[J]. Journal of Turbomachinery, 1993, 115(2): 207-216. doi: 10.1115/92-gt-301
    [5]
    VAN INGEN J. The eN method for transition prediction. historical review of work at TU delft: AIAA 2008-3830 [R]. Seattle, Washington: 38th Fluid Dynamics Conference and Exhibit, 2008.
    [6]
    ABU-GHANNAM B J, SHAW R. Natural transition of boundary layers: the effects of turbulence, pressure gradient, and flow history[J]. Journal of Mechanical Engineering Science, 1980, 22(5): 213-228.
    [7]
    DUNN M G. Convective heat transfer and aerodynamics in axial flow turbines[J]. Journal of Turbomachinery, 2001, 123(4): 637-686. doi: 10.1115/1.1397776
    [8]
    WALTERS D K, LEYLEK J H. A new model for boundary layer transition using a single-point RANS approach[J]. Journal of Turbomachinery, 2004, 126(1): 193-202. doi: 10.1115/1.1622709
    [9]
    LANGTRY R B, MENTER F R, LIKKI S R, et al. A correlation-based transition model using local variables: Part Ⅱ test cases and industrial applications[J]. Journal of Turbomachinery, 2006, 128(3): 423-434. doi: 10.1115/1.2184353
    [10]
    WALTERS D K, COKLJAT D. A three-equation eddy-viscosity model for Reynolds-averaged navier-stokes simulations of transitional flow[J]. Journal of Fluids Engineering, 2008, 130(12): 121401. doi: 10.1115/1.2979230
    [11]
    FU Song, WANG Liang. RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory[J]. Progress in Aerospace Sciences, 2013, 58: 36-59. doi: 10.1016/j.paerosci.2012.08.004
    [12]
    MENTER F R, SMIRNOV P E, LIU Tao, et al. A one-equation local correlation-based transition model[J]. Flow, Turbulence and Combustion, 2015, 95(4): 583-619. doi: 10.1007/s10494-015-9622-4
    [13]
    夏陈超, 姜婷婷, 郭中州, 等. 压缩性修正对γ-Reθ转捩模型的影响研究[J]. 空气动力学学报, 2015, 33(5): 603-609. XIA Chenchao, JIANG Tingting, GUO Zhongzhou, et al. Effects of compressibility correction on γ-Reθ transition model[J]. Acta Aerodynamica Sinica, 2015, 33(5): 603-609. (in Chinese doi: 10.7638/kqdlxxb-2014.0068

    XIA Chenchao, JIANG Tingting, GUO Zhongzhou, et al. Effects of compressibility correction on γ-Reθ transition model[J]. Acta Aerodynamica Sinica, 2015, 33(5): 603-609. (in Chinese) doi: 10.7638/kqdlxxb-2014.0068
    [14]
    张毅锋, 何琨, 张益荣, 等. Menter转捩模型在高超声速流动模拟中的改进及验证[J]. 宇航学报, 2016, 37(4): 397-402. ZHANG Yifeng, HE Kun, ZHANG Yirong, et al. Improvement and validation of Menter’s transition model for hypersonic flow simulation[J]. Journal of Astronautics, 2016, 37(4): 397-402. (in Chinese doi: 10.3873/j.issn.1000-1328.2016.04.004

    ZHANG Yifeng, HE Kun, ZHANG Yirong, et al. Improvement and validation of Menter’s transition model for hypersonic flow simulation[J]. Journal of Astronautics, 2016, 37(4): 397-402. (in Chinese) doi: 10.3873/j.issn.1000-1328.2016.04.004
    [15]
    WANG Yutian, LI Yiwen, XIAO Lianghua, et al. Similarity-solution-based improvement of γ-Re model for hypersonic transition prediction[J]. International Journal of Heat and Mass Transfer, 2018, 124: 491-503. doi: 10.1016/j.ijheatmasstransfer.2018.03.092
    [16]
    刘清扬, 雷娟棉, 刘周, 等. 适用于可压缩流动的γ-Reθt-fRe转捩模型[J]. 航空学报, 2022, 43(8): 125794. LIU Qingyang, LEI Juanmian, LIU Zhou, et al. γ-Reθt-fRe transition model for compressible flow[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(8): 125794. (in Chinese

    LIU Qingyang, LEI Juanmian, LIU Zhou, et al. γ-Reθt-fRe transition model for compressible flow[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(8): 125794. (in Chinese)
    [17]
    向星皓, 张毅锋, 袁先旭, 等. C-γ-Reθ高超声速三维边界层转捩预测模型[J]. 航空学报, 2021, 42(9): 625711. XIANG Xinghao, ZHANG Yifeng, YUAN Xianxu, et al. C-γ-Reθ model for hypersonic three-dimensional boundary layer transition prediction[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 625711. (in Chinese

    XIANG Xinghao, ZHANG Yifeng, YUAN Xianxu, et al. C-γ-Reθ model for hypersonic three-dimensional boundary layer transition prediction[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 625711. (in Chinese)
    [18]
    ECKERT E R G. Engineering relations for heat transfer and friction in high-velocity laminar and turbulent boundary-layer flow over surfaces with constant pressure and temperature[J]. Journal of Fluids Engineering, 1956, 78(6): 1273-1283. doi: 10.1115/1.4014011
    [19]
    ARTS T, LAMBERT DE ROUVROIT M, RUTHERFORD A W. Aero-thermal investigation of a highly loaded transonic linear turbine guide vane cascade. A Test Case for Inviscid and Viscous Flow Computations[J]. NASA STI/Recon Technical Report N, 1990, 91: 23437. doi: 10.1115/90-gt-358
    [20]
    郭隽, 刘丽平, 徐晶磊, 等. γ-Reθt转捩模型在跨声速涡轮叶栅中的应用[J]. 推进技术, 2018, 39(9): 1994-2001. GUO (Juan| Jun), LIU Liping, XU Jinglei, et al. Application of γ-(R)eθt transition model in transonic turbine cascades[J]. Journal of Propulsion Technology, 2018, 39(9): 1994-2001. (in Chinese doi: 10.13675/j.cnki.tjjs.2018.09.009

    GUO (Juan| Jun), LIU Liping, XU Jinglei, et al. Application of γ-(R)eθt transition model in transonic turbine cascades[J]. Journal of Propulsion Technology, 2018, 39(9): 1994-2001. (in Chinese) doi: 10.13675/j.cnki.tjjs.2018.09.009
    [21]
    CHESNAKAS C J. Experimental studies in a supersonic through-flow fan blade cascade[D]. Blacksburg, US: Virginia Tech, 1991.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2549.0KB)
    XML

    Article Metrics

    Article views (550) PDF downloads(23) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return