Volume 29 Issue 5
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Article Navigation >  Journal of Aerospace Power  > 2014  >  (5): 1053-1061
ZHENG Hai-fei, TANG Hao, LI Ming, MO Da. Overall performance and combustion organization based on turbine inter-vane burning technology[J]. Journal of Aerospace Power, 2014, (5): 1053-1061.
Citation: ZHENG Hai-fei, TANG Hao, LI Ming, MO Da. Overall performance and combustion organization based on turbine inter-vane burning technology[J]. Journal of Aerospace Power, 2014, (5): 1053-1061.
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Overall performance and combustion organization based on turbine inter-vane burning technology

  • 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. China Aviation Engine Establishment, Aviation Industry Corporation of China, Beijing 100009, China;

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

  • Received Date: 2013-02-24
  • Publish Date: 2014-05-28
    Abstract
  • The turbine inter-vane burning technology was applied to achieve the purpose of high thrust-weight ratio, low specific fuel consumption, low pollution and expanded stable working range of aero-engine. For this purpose, the burner placed between the turbine vanes was reheated to increase the gas temperature in the turbine, and then improve the overall performance of aero-engine. This works elaborated the potential advantage of the turbine inter-vane burning technology of enhancing the aero-engine overall performance based on overall thermodynamic cycle performance analysis, helping to research key technology, parameters and mechanism problem about combustion in this technology. And it is observed that: (1) for the jet-swirl scheme, radial vane cavity plays a decisive role in temperature distribution at the exit of combustor, and combustion efficiency can be improved by reducing the equivalence ratio in combustion ring cavity while leading to lower pollutant emissions quantity of CO, UHC (unburned hydrocarbon), NOx; (2) the jet-vortex scheme has better combustion performance when the secondary jet-flow angle is 60 degrees.

     

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