Abstract: In order to study the effect of entrance airflow parameters on the performance of combustor, a solid fuel regression rate model is coupled to the quasi-one-dimensional flow equations, and a quasi-one-dimensional method of combustor design and analysis is proposed. The method is used to keep the parameters of flight environment invariable and change the the total pressure, total temperature and mach number at the entrance of combustor. The sizes and performance of combustor under different flow conditions are calculated by using the quasi-one dimensional design and analysis method. The result shows that the total pressure and total temperature of entrance airflow can be increased to improve the performance of combustor under the design flight condition, but the influence of the total temperature on its performance is more greater. Lower mach number can be used to reduce the heating loss and improve the performance of combustor. If the air mass flow rate and the step area ratio are constant, the total temperature and total pressure are increased and the Mach number is reduced to improve the fuel regression rate and reduce the combustion chamber length.

Key words: ordnance science and technology, scramjet, solid fuel, combustor, entrance airflow parameter