Volume 35 Issue 8
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SHANG Shengfei, XIANG Shuhong, JIANG Lixiang. Effect of different hole shapes on hypersonic counter-jet film cooling[J]. Journal of Aerospace Power, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006
Citation: SHANG Shengfei, XIANG Shuhong, JIANG Lixiang. Effect of different hole shapes on hypersonic counter-jet film cooling[J]. Journal of Aerospace Power, 2020, 35(8): 1612-1621. doi: 10.13224/j.cnki.jasp.2020.08.006
shu

Effect of different hole shapes on hypersonic counter-jet film cooling

doi: 10.13224/j.cnki.jasp.2020.08.006
  • 1.

    Beijing Institute of Spacecraft Environment Engineering,China Academy of Space Technology,China Aerospace Science and Technology Corporation，Beijing 100094,China

  • 2.

    National Key Laboratory of Science and Technology on ,Reliability and Environmental Engineering，,Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China

  • Received Date: 2020-01-09
  • Publish Date: 2020-08-28
    Abstract
  • The influences of different cooling holes at different mass flow rates on film cooling effect were studied by researching the relationship between the film cooling hole shape and counter jet flowing. The CFD method was used to study 4 kinds of working conditions of the cylindrical hole, the shrinkage hole, the expansion hole and the shrinkage-expansion hole under flight height 50 km, flight Mach number 15 condition. Results show that: under the small mass flow rate, long penetration model (LPM) will occur in the shrinkage hole and the cylindrical hole, unlike the case of the expansion hole and the shrinkage-expansion hole. With the increase of the jet mass flow rate, the jet will change from LPM mode to short penetration model (SPM) mode, and the cooling benefit will not appreciably increase with the increasing jet mass flow rate. Considering the changes of the whole working states, the expansion hole is a relatively stable and reliable film cooling hole in the counter-jet film cooling.

     

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