Volume 39 Issue 12
Dec.  2024
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SONG Wei, WANG Jianhua, YAO Ran, et al. Influence of typical parameters in laminated cooling structure on flow and heat transfer behaviors[J]. Journal of Aerospace Power, 2024, 39（12）：20230017 doi: 10.13224/j.cnki.jasp.20230017
Citation: SONG Wei, WANG Jianhua, YAO Ran, et al. Influence of typical parameters in laminated cooling structure on flow and heat transfer behaviors[J]. Journal of Aerospace Power, 2024, 39（12）：20230017 doi: 10.13224/j.cnki.jasp.20230017
shu

Influence of typical parameters in laminated cooling structure on flow and heat transfer behaviors

doi: 10.13224/j.cnki.jasp.20230017
  • 1.

    Department of Thermal Science and Energy Engineering，University of Science and Technology of China，Hefei 230026，China

  • 2.

    Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

  • Received Date: 2023-01-08
    Available Online: 2024-07-24
    Abstract

  • Numerical simulation of fluid and solid zones was carried out to obtain heat transfer and temperature of eight different laminate configurations. The low Reynolds number shear stress transport (SST) k-ω turbulence model was selected. The relative error between the surface average Nusselt number and the cooling effect experiment was only 0.15%. The influences of the porosity of impingement and film holes, blockage ratio of the ribs, the film hole shape, and film cooling arrangement mode on heat transfer behaviors were studied. For flow resistance, in the interior, the influence level of rib blocking ratio was higher than the impingement hole opening rate; whereas in the gas side, the film hole type was more important than the film porosity. The comprehensive influence levels ranked as film hole type, film porosity, impingement hole opening rate and heat transfer area of the rib. To decrease friction loss coefficient and increase cooling efficiency, the 1-9-5 laminate unit more suitable than the 1-2-4 laminate model for the high temperature environment and low coolant supply pressure ratio at the leading edges of turbine blades was obtained, which can effectively increase the blade temperature by 140 K.

     

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