Analysis of Scramjet Combustor Based on Constant Mach Number Heating Method

Abstract

In order to design the geometry of scramjet combustor, in this paper, the discrete term model of hydrocarbon fuel in combustion chamber is established to solve the coupling of gas phase and liquid phase, and the chemical equilibrium reaction of hydrocarbon fuel is considered. A one-dimensional lumped parameter performance calculation model based on integral form is established. On this basis, the design of the combustion chamber is designed by using the constant Maher number method, and the optimization surface design principle is proposed to optimize the configuration. The results show that there is an optimal Mach number in the combustion chamber under different flight conditions, which makes the engine performance best; On the basis of constant Mach number design, the optimization surface design method is proposed, which greatly improves the performance of the combustion chamber. By comparing the calculation results of the above two design methods, it is concluded that reasonable distribution of Mach number distribution in the combustion chamber can effectively reduce the total pressure and total temperature loss.