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Volume 38 Issue 5
May  2012
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Journal of Beijing University of Aeronautics and Astronautics  > 2012  >  38(5): 702-706.
Sun Jining, Deng Jing, Deng Hongwuet al. Structure design of a new cooling system combined micro channel and film cooling in the turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(5): 702-706. (in Chinese)
Citation: Sun Jining, Deng Jing, Deng Hongwuet al. Structure design of a new cooling system combined micro channel and film cooling in the turbine blade[J]. Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(5): 702-706. (in Chinese)
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Structure design of a new cooling system combined micro channel and film cooling in the turbine blade

  • National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 28 Nov 2011
  • Publish Date: 30 May 2012
    Abstract
  • Numerical simulation was used to investigate a new compound cooling system, which combines micro channel and film cooling together in a guide turbine vane. Research was focused on the optimization design of these new organizational structures, in order to discuss the different effect on the characteristics of flow resistance and heat transfer. In these designed structures, branching channel structure in balancing cooling efficiency and the pressure loss has good effects. The computational results also show that the cooling efficiency of this compound cooling structure is higher than the cast-cooling blade. The prospect of the compound structure applied to turbine cooling system is huge.

     

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