Volume 30 Issue 4
Apr.  2015
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Article Navigation >  Journal of Aerospace Power  > 2015  >  30(4): 901-909
WU Fei, XIE Yi, SHAO Wan-ren, LIU Kun, RUAN Deng-fang, ZHENG Biao. Effect of inlet preswirl on the aerothermodynamic performance of splitter mixing exhaust system[J]. Journal of Aerospace Power, 2015, 30(4): 901-909. doi: 10.13224/j.cnki.jasp.2015.04.017
Citation: WU Fei, XIE Yi, SHAO Wan-ren, LIU Kun, RUAN Deng-fang, ZHENG Biao. Effect of inlet preswirl on the aerothermodynamic performance of splitter mixing exhaust system[J]. Journal of Aerospace Power, 2015, 30(4): 901-909. doi: 10.13224/j.cnki.jasp.2015.04.017
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Effect of inlet preswirl on the aerothermodynamic performance of splitter mixing exhaust system

doi: 10.13224/j.cnki.jasp.2015.04.017

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

  • 2. The State Key Laboratory of Mechanical Transmissions, Chongqing University, Chongqing 400044, China;

  • 3. College of Automotive Engineering, Chongqing University, Chongqing 400044, China

  • Received Date: 2013-11-07
  • Publish Date: 2015-04-28
    Abstract
  • In order to clarify the effect of core flow inlet preswirl angle of mixing exhaust system on the aerothermodynamic performance of splitter mixing exhaust system, investigation on the flow field of splitter mixing exhaust system at different inlet preswirl angles was carried through the three-dimensional numerical simulation based on Navier-Stokes equations, and the results were compared with flow along the axis. According to the results, the thickness of shear layer increases with the inlet preswirl angle, and it is the same with the twist of shear layer. Besides, at the splitter mixing exhaust system exit, as the inlet preswirl angle increases, the thermal mixing efficiency increase slightly and thermal mixing efficiency of 30 degree inlet preswirl angle model is 1.36 times the model with flow along the axis. Moreover, total pressure recovery coefficient and thrust of splitter mixing exhaust system also decline. Compared with the model with flow along the axis, the total pressure recovery coefficient of 30 degree inlet preswirl angle model falls by 0.0034 and its relative thrust declines by 0.081.

     

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