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低反力度对高负荷跨声风扇进口级的影响

宋西镇 周 盛 李秋实

宋西镇, 周 盛, 李秋实等 . 低反力度对高负荷跨声风扇进口级的影响[J]. 北京航空航天大学学报, 2008, 34(10): 1172-1176.
引用本文: 宋西镇, 周 盛, 李秋实等 . 低反力度对高负荷跨声风扇进口级的影响[J]. 北京航空航天大学学报, 2008, 34(10): 1172-1176.
Song Xizhen, Zhou Sheng, Li Qiushiet al. Impact of lower reaction on high aerodynamic load transonic fan inlet stage[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(10): 1172-1176. (in Chinese)
Citation: Song Xizhen, Zhou Sheng, Li Qiushiet al. Impact of lower reaction on high aerodynamic load transonic fan inlet stage[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(10): 1172-1176. (in Chinese)

低反力度对高负荷跨声风扇进口级的影响

基金项目: 国家自然科学基金资助项目(10577002)
详细信息
    作者简介:

    宋西镇(1977-),男,陕西宝鸡人,博士生,songxz@buaa.edu.cn.

  • 中图分类号: V211.6

Impact of lower reaction on high aerodynamic load transonic fan inlet stage

  • 摘要: 认为低反力度是提高跨声速风扇/压气机进口级气动负荷的必然结果.通过气动负荷系数和反力度的定义,得到了反力度随气动负荷系数的变化规律,并给出了气动负荷系数的两个临界值.以成功设计并实验验证的某单级高负荷风扇为基准,通过数值模拟对4组跨声速风扇转子方案进行比较研究.发现随着气动负荷系数的提高,转子轮毂区的气动参数分布发生了显著地变化.认为静子的展向跨声速来流是高气动负荷跨声速风扇进口级设计面临的一个问题.通过讨论,认为静子跨声速来流问题可能通过已有的设计手段解决.从研究方案中选取了一个最优的单级风扇方案,其气动负荷系数达到0.53,并分析了其三维粘性流场.

     

  • [1] Farmakalides C D, McKenzie A B, Elder R L. The effects of reaction on axial flow compressor performance . ASME 94-GT-456,1994 [2] Voit C H. Investigation of a high pressure ratio eight stage axial flow research compressor with two transonic inlet stage-I: aerodynamic design . NACA RM E53I24, 1953 [3] Sandercock D M, Kovach K, Lieblein S. Experimental investigation of a five stage axial flow research compressor with transonic rotors in all stages -I: compressor design . NACA RM E54F24, 1954 [4] Yu Qing, Li Qiushi, Li Ling. The experimental researches on improving operating stability of a single-stage transonic fan . ASME GT-2002-30640, 2002 [5] Wennerstrom A J, Frost G R. Design of a 1500 ft/sec transonic high through flow axial flow compressor with low hub/tip ratio . AD-B016386, 1971 [6] Wennerstrom A J, Hearsey R M. The design of axial compressor stage for a total pressure ratio of 3 to 1 . ARL-71-TR-0061,1971 [7] Wennerstrom A J, Puterbaugh S L. A three-dimensional model for the prediction of shock losses in compressor blade rows[J]. ASME Journal of Eng For Gas Turbines and Power, 1984, 106(2):295-299 [8] Gummer V, Wenger U, Kau H P. Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors[J]. Journal of Turbomachinery, 2001,123:40-48 [9] Friedrichs J, Baumgarten S, Kosyna G. Effect of stator design on stator boundary layer flow in a highly loaded single-stage axialvflow low-speed compressor[J]. Journal of Turbomachinery, 2001, 123:483-489
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出版历程
  • 收稿日期:  2007-11-01
  • 网络出版日期:  2008-10-31

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