Research on Geometry Configuration/Fuel Distribution of Combustion Chamber of Scramjet

摘要

In this article, based on the reference configuration of combustion chamber of scramjet, the influence of design point parameters of the two-stage combustion chamber geometry configuration and fuel distribution ratio on engine performance is studied, and thrust and specific impulse are used as the overall performance evaluation parameters, the comparison and evaluation of the mobility and economy of the engine provide certain references for the selection of design point parameters of the combustion chamber geometry configuration and fuel distribution ratio. The results show that increasing the area of the thermal throat of the combustion chamber by increasing the two-stage expansion ratio of the combustion chamber can increase the thrust at low speed and enhance the mobility of the aircraft; when it does not cause thermal choke and does not affect the start-up of the inlet, increasing the fuel distribution ratio in the first stage of the combustion chamber can increase the engine's specific impulse, thereby improve the economy of the aircraft.