In order to improve the combustion efficiency of gas-particle two-phase gas in the combustor of solid rocket scramjet, the influence of the combustor length on the combustion characteristics of gas-particle two-phase gas under Ma6 and 25km inlet flow was studied by numerical simulation. The results show that the main area of fuel combustion is the first expansion section. In addition, part of the fuel is also burned in the equal straight section, which can maintain a high working pressure for the first expansion section to improve the combustion efficiency of the combustor. The second expansion section is conducive to gas expansion work and improves the total pres-sure recovery coefficient. The numerical results show that the gas phase components in the fuel-rich gas can burn quickly after entering the combustor, and the combustion efficiency of the granular phase fuel is the main factor determining the total combustion efficiency of the fuel. The combustion mode is determined by the heat release intensity of gas-particle two-phase gas in the combustor.
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Zhao et al. (2024) studied this question.
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