Volume 22 Issue 5
May  2007
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2007  >  22(5): 808-813
LIU Xiao-lan, GU Chuan-gang, Yang Bo, Wang Tong, XING Wei-dong, ZHANG Ji-zhong. Loss models and loss analysis of variable geometry radial inflow turbine[J]. Journal of Aerospace Power, 2007, 22(5): 808-813.
Citation: LIU Xiao-lan, GU Chuan-gang, Yang Bo, Wang Tong, XING Wei-dong, ZHANG Ji-zhong. Loss models and loss analysis of variable geometry radial inflow turbine[J]. Journal of Aerospace Power, 2007, 22(5): 808-813.
shu

Loss models and loss analysis of variable geometry radial inflow turbine

  • 1.

    Key Laboratory for Power Machinery and Engineering of the Ministry of Education of China, Shanghai Jiao Tong University, Shanghai 200030, China

  • 2.

    National Laboratory of Diesel-Engine Turbocharging Tech.Datong 037036, China

  • Received Date: 2006-04-21
  • Rev Recd Date: 2006-10-30
  • Publish Date: 2007-05-28
    Abstract
  • Based on the experimental data of a 99 mm rotor,various losses and loss models of the stator of variable geometry radial inflow turbine(VGT) was analyzed.Also,a quantitative analysis was performed for the incidence loss in VGT's stator.When calculating the blade passage loss,Glassman loss model was proved to match the test results by calculating comparatively the boundary layer friction loss in blade row with different stator throat widths.The trailing-edge loss of radial inflow turbine stator was discussed based on the loss models of NASA,showing that the loss increases linearly with the trailing edge thickness.Thus,an efficient method of reducing trailing-edge loss is to cut down the trailing edge thickness.

     

    • FullText(HTML)
  • loading
    • References(15)
  • [1]
    Hiett G F,Johnston I H.Experiments concerning the aerodynamic performance of inward flow radial turbines[J].Proc.Instn.Mech.Engrs,Part A.1963,178:28-42.
    [2]
    Spence S W T,Artt D A.Experimental performance evaluation of a 99mm radial inflow nozzled turbine with different stator throat areas[J].Journal of Power and Energy,1997,Part A,478-487.
    [3]
    Spence S W T,Doran W J,Artt D W.Experimental performance evaluation of a 99mm radial inflow nozzled turbine at larger stator-rotor throat area ratios.[J] Journal of Power and Energy,1999,213,Part A,207-215.
    [4]
    Artt D W,Spence S W T.A loss analysis based on experimental data for a 99mm radial inflow nozzled turbine with different stator throat areas[J].Journal of Power and Energy,1998,212,Part A,28-31.
    [5]
    Wallance F J.Theoretical assessment of the performance characteristics of inward radial flow turbines[J].Proc.Instn.Mech.Engrs,1958,172,931-952.
    [6]
    Todd C A,Futral S M Jr.A fortran program to estimate the off-design performance of radial-inflow turbines[R].NASA TN D-5059,1969:2-29.
    [7]
    Wasserbauer C A,Glassman A J.Fortran program for predicting off-design performance of radial-inflow turbines.[R] NASA TN D-8063.1975:3-7.
    [8]
    Meitner P L,Glassman A J.Loss model for off-design performance analysis of radial inflow turbines with pivoting-vane,variable-area stators.[R] NASA TM-81532,1980:2-11.
    [9]
    Kofskey M G,Nusbaum W J.Effects of specific speed on experimental performance of a radial-inflow turbine[R].NASA TN D-6605.1972:3-24.
    [10]
    Conrad O,Raif K,Wessels M.The calculation of performance maps for centrifugal compressors with vane-island diffusers[A].Perform Predict of Centrifugal Pumps and Compressors,Presented at Annu Int Gas Turbine Conf and Exhib,25th and Annu Fluids Eng Conf,22nd[C].New Orleans,LA,USA,ASME,1980:135-147.
    [11]
    Arduzzon G,Pavesi G.Optimum incidence angle in centrifugal pumps and radial inflow turbines[J].Proceedings of the Institution of Mechanical Engineers,Part A,Journal of Power and Energy,Vol.212,Issue 2,1998:98-102.
    [12]
    Futral S M Jr,Charles W.Off-design performance prediction with experimental verification for a radial-inflow turbine[R].NASA TN D-2621,1965:1-22.
    [13]
    Rohlik A H E.Determination of radial inflow turbine design geometry for maximum efficiency[R].NASA TN D-4384,1968:16-28.
    [14]
    Glassman A J.Computer program for design analysis of radial-inflow turbines[R].NASA TN D-8164.1976:2-19.
    [15]
    Prust H W Jr.Boundary-layer losses.Ch.7 of turbine design and application,Vol.2,Glassman A J[R].NASA SP-290,1973:195-221.
    • 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(607.0KB)
    XML

    Article Metrics

    Article views (1899) PDF downloads(575) 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