Volume 26 Issue 5
May  2011
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JIN Dong-hai, GUI Xing-min. Numerical simulation of highly loaded multi-stage fan / compressor of a turbofan engine[J]. Journal of Aerospace Power, 2011, 26(5): 1059-1065.
Citation: JIN Dong-hai, GUI Xing-min. Numerical simulation of highly loaded multi-stage fan / compressor of a turbofan engine[J]. Journal of Aerospace Power, 2011, 26(5): 1059-1065.

Numerical simulation of highly loaded multi-stage fan / compressor of a turbofan engine

  • Received Date: 2010-09-28
  • Rev Recd Date: 2011-03-03
  • Publish Date: 2011-05-28
  • According to high-altitude and low Reynolds number aerodynamic performance requirements of a turbofan engine, the fan/compressor on 0km and 21km operating conditions were simulated using three-dimensional (3-D) numerical simulation software Numeca. The results show that: the three-dimensional numerical simulation results of the 4-stage fan are in good agreement with the experimental results, and the precision can meet the engineering requirements; from 0km to 21km altitude, the inlet blade chord Reynolds number is reduced from 106 to 105, the mass flow rate is reduced by 2%~3%, the total pressure ratio is decreased a bit, and the efficiency is decreased by 3%; in the 3-D numerical simulation of 9-stage compressor, air bleeding is considered; from 0km to 21km altitude, the inlet blade chord Reynolds number is also reduced from 106 to 105, the mass flow rate and total pressure ratio are decreased a bit, and the attenuation of adiabatic efficiency increases from 4% to 7% with the decrease of speed.

     

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