Volume 26 Issue 7
Jul.  2011
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DENG Hong-wu, XIAO Jun, LI Guo-qing, XUE Hang. Influence of blowing ratio on film cooling of rotating turbine blade[J]. Journal of Aerospace Power, 2011, 26(7): 1452-1457.
Citation: DENG Hong-wu, XIAO Jun, LI Guo-qing, XUE Hang. Influence of blowing ratio on film cooling of rotating turbine blade[J]. Journal of Aerospace Power, 2011, 26(7): 1452-1457.
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Influence of blowing ratio on film cooling of rotating turbine blade

  • 1.

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

  • 2.

    Market Department of China National Aero-Technology Import and Export Corporation, Beijing 100101,China

  • Received Date: 2010-07-02
  • Rev Recd Date: 2010-11-02
  • Publish Date: 2011-07-28
    Abstract
  • Experimental investigations were carried out to study the rotating film cooling characteristics at different blowing ratios in a 1.5-turbine stage.The mainstream Reynolds number Reg is 1.6451×105 in the experiment.CO2 acts as a coolant with mainstream jet density ratio of 1.57.Turbine speed is 475r/min,and the rotation number is 1.901.The blowing ratio varies from 0.5 to 2.0.By using steady-state liquid crystal method,the results show that: (1) On pressure side,the film cooling efficiency and the film coverage increase,the deflection angle of film trajectory decreases with the increasing blowing ratio. (2) On suction side,the film cooling efficiency and the film coverage first increase and then decrease,the film trajectory has no obvious deflection angle with the increasing blowing ratio. (3) The curvature radius of jet flow affects the adhesion of film on the wall.

     

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    • References(13)
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