Volume 29 Issue 4
Apr.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  29(4): 907-916
ZHONG Yi-cheng, ZHANG Cun-yuan, XU Wei-zu, PAN Shang-neng. Numerical study guide vane coolant on performance of turbine stage[J]. Journal of Aerospace Power, 2014, 29(4): 907-916. doi: 10.13224/j.cnki.jasp.2014.04.023
Citation: ZHONG Yi-cheng, ZHANG Cun-yuan, XU Wei-zu, PAN Shang-neng. Numerical study guide vane coolant on performance of turbine stage[J]. Journal of Aerospace Power, 2014, 29(4): 907-916. doi: 10.13224/j.cnki.jasp.2014.04.023
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Numerical study guide vane coolant on performance of turbine stage

doi: 10.13224/j.cnki.jasp.2014.04.023

  • 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;

  • 2. Technical Department, the Limited Company of Nanjing Puguo Technology,Nanjing 210016,China;

  • 3. Chinese Avation Powerplant Research Institution, Aviation Industry Corporation of China,Zhuzhou Hunan 412002,China

  • Received Date: 2013-02-27
  • Publish Date: 2014-04-28
    Abstract
  • Numerical simulation on a three-dimensional twisty high-pressure gas turbine guide vane with the whole body coolant injection was conducted. Detailed analysis of different coolant injection rate affect the blade aerodynamic performance, cooling efficiency and cascade channel loss was performed at the condition of design speed. Comparative analysis was made to learn the influence of changed rotational speed on the performance of turbine stage at the same coolant injection rate. The results show: different coolant injection rate affect static pressure near holes area more obviously, while the impact on the downstream of rotor surface static pressure is very little. Guide vane coolant injection has less influence on the mainstream flow angle in the cascade channel. Coolant injection rate increased from 2.50% of main flow rate to 6.25%, the adiabatic temperature of the blade surface dropped by 11.19%, total pressure loss and energy loss of guide vanes cascade channel increased 12.95% and 12.01% respectively, while the turbine stages power and efficiency dropped by 2.39% and 1.51% respectively.

     

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