Volume 29 Issue 5
May  2014
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SHANG Shou-tang, GAO Xian-zhi, GUO Rui-qing, GUO Da-peng, GAO Wei-wei, LI Feng. Capability prediction of high temperature rise center-staged combustor[J]. Journal of Aerospace Power, 2014, (5): 1001-1007.
Citation: SHANG Shou-tang, GAO Xian-zhi, GUO Rui-qing, GUO Da-peng, GAO Wei-wei, LI Feng. Capability prediction of high temperature rise center-staged combustor[J]. Journal of Aerospace Power, 2014, (5): 1001-1007.
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Capability prediction of high temperature rise center-staged combustor

  • School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 2013-07-10
  • Publish Date: 2014-05-28
    Abstract
  • Based on the increasing demand for high temperature rise combustor of high thrust-mass-ratio aeroengine, a design method of center-staged combustor was given and three-dimensional numerical simulation was conducted on the design model using the same diffuser, outer case and exit dimensions of single annular combustor. The capability of center-staged combustor was compared and analyzed with the numerical simulation results and experimental results obtained from single annular combustor. The results show that, by using the center-staged combustor, the total pressure recovery coefficient can be improved compared with the single annular combustor, and the outlet temperature distribution factor (OTDF) of the combustor is lower than that of single annular combustor in addition to higher temperature rise, but the CO and NO emissions are higher than that of single annular combustor in slow train state. At the designed 0.045 fuel/air ratio state, the temperature rise can reach 1360K, and the total pressure recovery coefficient is no less than 0.96; OTDF can be no more than 0.14; the radial temperature distribution factor (RTDF) at outlet can be no more than 0.10, with the combustion efficiency no less than 0.987.

     

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