Volume 22 Issue 2
Feb.  2007
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Article Navigation >  Journal of Aerospace Power  > 2007  >  22(2): 187-192
DING Shui-ting, CUI Liang, SUN Ji-ning, TAO Zhi, XU Guo-qiang, LI Qiu-shi. Combined features of the inner impingement and outer film cooling holes of a vane[J]. Journal of Aerospace Power, 2007, 22(2): 187-192.
Citation: DING Shui-ting, CUI Liang, SUN Ji-ning, TAO Zhi, XU Guo-qiang, LI Qiu-shi. Combined features of the inner impingement and outer film cooling holes of a vane[J]. Journal of Aerospace Power, 2007, 22(2): 187-192.
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Combined features of the inner impingement and outer film cooling holes of a vane

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

  • Received Date: 2006-01-17
  • Rev Recd Date: 2006-05-09
  • Publish Date: 2007-02-28
    Abstract
  • Numerical simulation has been used to investigate a cooling configuration of a guide turbine vane.This vane has outer sparse film cooling holes and inner impingement holes.In this paper,we mainly studied how different positions and diameters of the film cooling holes influenced the cooling efficiency on the pressure and suction sides of the vane;and discussed the cooling efficiency and uniformity of temperature distribution on the pressure and suction sides of the vane.The computational results show that,within the parameters used in this simulation,the increase in the film cooling hole diameters obviously improves the cooling efficiency on the pressure side of the vane,but the effect is more complicated on the suction side.Considering the cooling efficiency and the uniformity of temperature distribution on the pressure and suction sides of the vane,the position of the film cooling holes located on the front side of the chamber results in the best cooling efficiency.

     

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