Volume 36 Issue 5
May  2021
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LIN Aqiang, ZHENG Qun, XIA Quanzhong, ZHANG Hai, LIU Gaowen. Pre-cooling characteristics of high temperature inlet air for turbine power combined with ramjet[J]. Journal of Aerospace Power, 2021, 36(5): 987-996. doi: 10.13224/j.cnki.jasp.2021.05.010
Citation: LIN Aqiang, ZHENG Qun, XIA Quanzhong, ZHANG Hai, LIU Gaowen. Pre-cooling characteristics of high temperature inlet air for turbine power combined with ramjet[J]. Journal of Aerospace Power, 2021, 36(5): 987-996. doi: 10.13224/j.cnki.jasp.2021.05.010
shu

Pre-cooling characteristics of high temperature inlet air for turbine power combined with ramjet

doi: 10.13224/j.cnki.jasp.2021.05.010
  • 1.

    School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China

  • 2.

    Shanxi Key Laboratory of Thermal Science in Aero-engine System,Northwestern Polytechnical University,Xi’an 710072,China

  • 3.

    College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China

  • 4.

    Science and Technology on Altitude Simulation Laboratory,Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621700,China

  • Received Date: 2020-08-11
  • Publish Date: 2021-05-28
    Abstract
  • To solve the negative effect of high temperature inlet air on the turbo engine performance in the turbine-based ramjet combined cycle engine, numerical analysis on the pre-cooling section of a real high-altitude simulation experiment was carried out. Based on the Eulerian-Lagrangian multiphase flow method, the heat and mass transfer process of gas-liquid two-phase was analyzed. And then, the temperature and pressure fields in the pre-cooling section were explored at different high altitudes and high Mach number inlet air conditions. Results showed that mass injection had an obvious improvement on temperature drop. The flow loss in the pre-cooling section with injection device was mainly caused by the dissipative entropy production due to the viscous dissipation, while the heating entropy production caused by the temperature gradient change of the flow field due to the gas-liquid heat transfer temperature difference was not significant. By comparing the cooling effect of 4%-7% water/air ratio at the high-altitude simulation inlet air conditions, it can be discovered that the airflow temperature drop in the pre-cooling section was within the range of 32.30-90.08 K, and the total pressure drop coefficient was reduced from 1.42%-1.86% to 0.95%-1.46% before and after mass injection cooling. Therefore, mass injection cooling can improve inlet air flow field characteristics of turbine engine at high altitude and high Mach number.

     

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