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Volume 34 Issue 01
Jan.  2008
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Journal of Beijing University of Aeronautics and Astronautics  > 2008  >  34(01): 51-54.
Yang Bin, Xu Guoqiang, Ding Shuiting, et al. Numerical study for film cooling characteristics on rotating model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(01): 51-54. (in Chinese)
Citation: Yang Bin, Xu Guoqiang, Ding Shuiting, et al. Numerical study for film cooling characteristics on rotating model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(01): 51-54. (in Chinese)
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Numerical study for film cooling characteristics on rotating model

  • National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 22 Jan 2007
  • Publish Date: 31 Jan 2008
    Abstract
  • Computations were performed to simulate the two rows of 90° staggered holes film cooling characteristics over a rotating turbine blade model both on leading and trailing surfaces. The influences of the Reynolds number Re, rotation number Rt and the blowing ratio M on the film cooling effectiveness η and discharge coefficient Cd distributions were presented. Results show that the coolant is influenced by the centrifugal force and Coriolis force to deflect towards the high-radius locations, and this will lead to low values of η . The enhancement of Re can impair the film cooling effectiveness, and the high values of M are not suitable for the thermal protection near the exit of cooling holes. All the discharge coefficients increase with the augmentation of M , and decrease with the increase of Rt . Moreover, the Cd values beside trailing surface are much higher than that beside the leading surface under the same operating conditions.

     

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