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.