Volume 23 Issue 7
Jul.  2008
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Article Navigation >  Journal of Aerospace Power  > 2008  >  23(7): 1334-1340
JIN Shao-shan, JIANG Pei-xue, SUN Ji-guo. Investigation on the transpiration cooling of a liquid rocket nozzle[J]. Journal of Aerospace Power, 2008, 23(7): 1334-1340.
Citation: JIN Shao-shan, JIANG Pei-xue, SUN Ji-guo. Investigation on the transpiration cooling of a liquid rocket nozzle[J]. Journal of Aerospace Power, 2008, 23(7): 1334-1340.
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Investigation on the transpiration cooling of a liquid rocket nozzle

  • 1.

    Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

  • 2.

    Beijing Aerospace Propulsion Institute, Beijing, 100076, China

  • Received Date: 2007-06-26
  • Rev Recd Date: 2007-10-31
  • Publish Date: 2008-07-28
    Abstract
  • The SSTk-ω turbulence model was used to simulate the coupled whole field of the transpiration cooling of a Laval-nozzle of a liquid O2/H2 propellant rocket engine.The influences of porosity,variation property,compressibility,the thermal disperse effect of porous media,micro-scale flow and mass transfer were considered in the model.The influences of porosity on local blowing ratio,the wall temperature and the boundary layer thickness were analyzed and compared with the regenerative cooling.The results showed that the increase of average blowing ratio can decrease the average wall temperature with a larger proportion and for the transpiration cooling nozzle the throat is no longer the highest temperature point.The simulation results were compared with both the experimental results and the one dimension aerodynamics formula and approved to be accurate.

     

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