Volume 29 Issue 4
Apr.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  29(4): 737-747
YANG Zhi-min, JIA Zhen, ZHAO Yu, ZHANG Shu-hua, GE Xin. Numerical simulation of flow and heat transfer performance in turntable[J]. Journal of Aerospace Power, 2014, 29(4): 737-747. doi: 10.13224/j.cnki.jasp.2014.04.001
Citation: YANG Zhi-min, JIA Zhen, ZHAO Yu, ZHANG Shu-hua, GE Xin. Numerical simulation of flow and heat transfer performance in turntable[J]. Journal of Aerospace Power, 2014, 29(4): 737-747. doi: 10.13224/j.cnki.jasp.2014.04.001
shu

Numerical simulation of flow and heat transfer performance in turntable

doi: 10.13224/j.cnki.jasp.2014.04.001

  • 1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;

  • 2. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China,Shenyang 110015,China;

  • 3. Aerospace Engine Research Institute, Aviation Industry Corporation of China,Beijing 100083,China

  • Received Date: 2013-05-16
  • Publish Date: 2014-04-28
    Abstract
  • For coolant water path of turntable scoured by hot gas at combustor exit, two-dimensional and three-dimensional physical models of were established to simulate the flow and heat transfer process in internal path. The effect of inlet pressure and mass flow of coolant water on flow resistant and heat transfer performance was investigated. The results show that: (1) increasing inlet pressure of coolant water has little influence on wall temperature of turntable, and the wall temperature of structure 1 increases by 5K and the wall temperature of structure 2 increases by 7K when the inlet pressure of coolant water of turntable increases from 2.3×105Pa to 8.3×105Pa; (2) the wall temperature of structure 1 decreases about 120K and the wall temperature of structure 2 decreases about 100K when the inlet velocity of coolant water increases from 0.5m/s to 5.3m/s; the cooling effect is obvious; (3) shortening passage area of structure 2 will gain better heat transfer effect with the smaller mass flow of coolant water.

     

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    • References(16)
  • [1]
    彭建,白雪.航空发动机燃烧室温度测量[J].燃气涡轮试验与研究,2000,13(2):50-52.
    [2]
    左渝钰.航空发动机高温应变测量系统[J].计算机测量与控制,2008,16(11):1528-1529. ZUO Yuyu.Strain measuring system depending on high temperature of aero-engine[J].Computer Measurement & Control,2008,16(11):1528-1529.(in Chinese)
    [3]
    丁国玉,何小民,金义,等.主燃区出口特征影响出口温度场性能的数值研究[J].航空发动机,2012,38(4):17-21. DING Guoyu,HE Xiaomin,JIN Yi,et al.Influence of primary zone outlet feature on combustor outlet tempetature field[J].Aeroengine,2012,38(4):17-21.(in Chinese)
    [4]
    富丽新,张宝诚,赵春伟.航空发动机燃烧室和涡轮出口滞止温度相关的研究[J].航空动力学报,1996,11(2):202-204. FU Lixin,ZHANG Baocheng,ZHAO Chunwei.Relationship of turbine-outlet temperature to combustor-outlet temperature in aeroengine[J].Journal of Aerospace Power,1996,11(2):202-204.(in Chinese)
    [5]
    杨志民,孙永飞,赵煜,等.航空发动机燃烧室出口温度场双向测量方法[J].航空发动机,2010,36(1):41-44. YANG Zhimin,SUN Yongfei,ZHAO Yu,et al.Bi-directional measurement method of combustor outlet tempetature field for aero-engine[J].Aeroengine,2010,36(1):41-44.(in Chinese)
    [6]
    徐榕,程明,赵坚行,等.斜切径向旋流器环形燃烧室数值模拟[J].航空发动机,2010,36(2):45-49. XU Rong,CHENG Ming,ZHAO Jianxing,et al.Numerical study of an annular gas combustor with swirl cup[J].Aeroengine,2010,36(2):45-49.(in Chinese)
    [7]
    吴超,徐让书,蒲宁,等.某型航空发动机燃烧室出口温度场数值模拟[J].沈阳航空工业学院学报,2009,26(2):1-4. WU Chao,XU Rangshu,PU Ning,et al.Numerical simulation of an aero-engine combustor exit temperature field[J].Journal of Shenyang Institute of Aeronautical Engineering,2009,26(2):1-4.(in Chinese)
    [8]
    虞跨海,王金生,杨茜,等.回流式冷却叶片流热耦合数值分析[J].热能动力工程,2011,26(3):271-274. YU Kuahai,WANG Jinsheng,YANG Xi,et al.Numerical simulation of the fluid/heat coupling in return flow type cooling blades[J].Journal of Engineering for Thermal Energy and Power,2011,26(3):271-274.(in Chinese)
    [9]
    王利平,张靖周,姚玉.敷设热障涂层气冷叶片温度分布数值研究[J].航空动力学报,2012,27(2):357-364. WANG Liping,ZHANG Jingzhou,YAO Yu.Numerical investigation on tempetature distribution of an air-cooled and thermal barrier coating blade[J].Journal of Aerospace Power,2012,27(2):357-364.(in Chinese)
    [10]
    吉倩,赵晨光,张宝诚,等.航空发动机燃烧室过渡态温度场数值研究[J].沈阳航空工业学院学报,2010,27(2):24-28. JI Qian,ZHAO Chenguang,ZHANG Baocheng,et al.Numerical simulation of the temperature field in transition condition of an aero-engine combustor[J].Journal of Shenyang Institute of Aeronautical Engineering,2010,27(2):24-28.(in Chinese)
    [11]
    宋少雷,李铜桥,李金英.有气膜孔燃气轮机燃烧室燃烧流场的数值模拟[J].热能动力工程,2010,25(3):269-272. SONG Shaolei,LI Tongqiao,LI Jinying.Numerical calculation of the combustion flow field in a gas turbine combustor with air-film holes[J].Journal of Engineering for Thermal Energy and Power,2010,25(3):269-272.(in Chinese)
    [12]
    尹洪,王文萍,任静,等.燃烧室出口辐射对气膜冷却传热影响研究[J].工程热物理学报,2012,33(2):214-217. YIN Hong,WANG Wenping,REN Jing,et al.Research on the effect of combustor outlet radiation on the film cooling heat transfer[J].Journal of Engineering Thermophysics,2012,33(2):214-217.(in Chinese)
    [13]
    乔娟,张宝诚,吕文菊,等.航空发动机燃烧室火焰筒掺混区特性的研究[J].沈阳航空工业学院学报,2007,24(3):1-4. QIAO Juan,ZHANG Baocheng,LV Wenju,et al.Dilution-zone characteristics of an aero-engine combustor flame tube[J].Journal of Shenyang Institute of Aeronautical Engineering,2007,24(3):1-4.(in Chinese)
    [14]
    何跃龙,邓远灏,颜应文,等.大涡模拟模型燃烧室燃烧性能计算[J].航空动力学报,2012,27(9):1939-1947. HE Yuelong,DENG Yuanhao,YAN Yingwen,et al.Large-eddy simulation of two-phase reacting flows and combustion performance in model combustor[J].Journal of Aerospace Power,2012,27(9):1939-1947.(in Chinese)
    [15]
    徐丽,孙丽艳.某型燃气轮机燃烧室性能数值模拟[J].汽轮机技术,2012,54(2):117-119. XU Li,SUN Liyan.Numerical simulation of combustor performance of gas turbine[J].Turbine Technology,2012,54(2):117-119.(in Chinese)
    [16]
    周昆原,罗翔,徐国强.旋转诱导燃气入侵的数值模拟[J].航空动力学报,2011,26(12):2704-2709. ZHOU Kunyuan,LUO Xiang,XU Guoqiang.Numerical simulation of rotationally-induced ingress through turbine rim seals[J].Journal of Aerospace Power,2011,26(12):2704-2709.(in Chinese)
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