| Citation: | SHI Yinuo, SHAN Yong, TAN Xiaoming, et al. Supercritical pressure fuel cooling characteristics of ramjet nozzle[J]. Journal of Aerospace Power, 2024, 39（10）：20220704 doi: 10.13224/j.cnki.jasp.20220704
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On the premise of obtaining typical heat load of the ramjet nozzle and its heat transfer boundary conditions, a longitudinally ribbed supercritical pressure fuel cooling multi-channel structure was constructed, the effects of fuel flow direction, fuel flow (68—204 g/s), fuel inlet temperature (300—640 K), fuel supercritical pressure (3—5 MPa) on the flow and heat transfer characteristics of supercritical pressure fuel in the channel were compared and analyzed. The results showed that: the supercritical pressure fuel consumption was 275 g/(s·m2), the maximum temperature of the nozzle wall can be reduced from 2 986 K to below 1 200 K; when the fuel and gas flow in the nozzle were in the same direction, the inlet section effect of the fuel heat exchange can be fully utilized to reduce the high temperature of the nozzle inlet wall, the temperature difference between the nozzle inlet and outlet walls was reduced, and the axial thermal stress can be reduced; the fuel mass flow increased, the surface heat transfer coefficient in the cooling channel increased, and the cooling effect improved, but the fuel pressure drop gradually increased; if the fuel inlet temperature was too high, the thermal diffusivity of the fluid near the channel wall increased sharply, resulting in heat transfer deterioration, then there was an optimal inlet temperature to minimize the fuel pressure drop; when the fuel inlet temperature was low, the gas side wall surface temperature and fuel pressure drop were not sensitive to the change of fuel pressure.
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