Analysis of overall performance of multi-stage combustor scramjet engine

Abstract

In this paper, based on the scramjet, by the mode of characteristic calculation of one-dimensional scramjet engine, the effect of three and four-section combustion chamber geometry, fuel distribution ratio on scramjet performance is studied. The results of the comparison and evaluation of engine performance provide a certain reference for the geometric configuration of the combustion chamber and fuel injection parameters of the design point. It is mainly to determine the appropriate combustion chamber geometry and fuel injection method to obtain better combustion chamber performance and overall engine performance. The results show that increasing the thermal throat area of the combustion chamber can effectively increase the thrust of the aircraft during low-speed flight condition, and increase the fuel distribution ratio and the length of the expansion section in the front section of the combustion chamber without thermal choke and without affecting the inlet start, can improve the specific impulse of the engine at high speed.