Volume 30 Issue 8
Aug.  2015
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Article Navigation >  Journal of Aerospace Power  > 2015  >  30(8): 1818-1825
DU Gui-xian, JIN Wen-dong, SHAO Wan-ren, DENG Hong-wei. Adjustment method of effective throat for axisymmetric vectoring exhaust nozzle[J]. Journal of Aerospace Power, 2015, 30(8): 1818-1825. doi: 10.13224/j.cnki.jasp.2015.08.004
Citation: DU Gui-xian, JIN Wen-dong, SHAO Wan-ren, DENG Hong-wei. Adjustment method of effective throat for axisymmetric vectoring exhaust nozzle[J]. Journal of Aerospace Power, 2015, 30(8): 1818-1825. doi: 10.13224/j.cnki.jasp.2015.08.004
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Adjustment method of effective throat for axisymmetric vectoring exhaust nozzle

doi: 10.13224/j.cnki.jasp.2015.08.004

  • Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

  • Received Date: 2014-01-23
  • Publish Date: 2015-08-28
    Abstract
  • Based on three-dimensional Reynolds-averaged Navier-Stokes equations, the interior flow field of axisymmetric vectoring exhaust nozzle was investigated numerically, and variation of effective throat and flux coefficient with vectoring deflection angles was analyzed at different nozzle pressure ratios. The results show that,when the vectoring deflection angle exceeds a certain value, effective throat position of the axisymmetric vectoring nozzle inclines, effective throat area reduces, and flux coefficient decreases with the increase of vectoring deflection angle and the decrease of nozzle pressure ratio. According to the results, an adjustment method of effective throat for axisymmetric vectoring exhaust nozzle used during nozzle vectoring is proposed by taking the nozzle pressure ratio and the vectoring deflection angle as input parameters; and the variation of flux coefficient is considered before and after adjusting the axisymmetric vectoring nozzle throat area. This method can provide a more accurate input for engine control system, improve the control accuracy with the flux variety less than 0.4%,and shorten by 10% of the adjustment time at least. The method can provide a reference for state regulation of thrust-vectoring engine.

     

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