Abstract
A quasi-one-dimensional model for scramjet combustor coupled with regenerative cooling has been developed for comprehensive and rapid prediction of engine performance in system design and further research of advanced scramjet engine cycles with regenerative cooling. The model consists of two sets of ordinary differential equations for the reacting flow in the combustor and the cooling flow in the cooling channels separately. Additional models for wall heat transfer, sonic fuel injection, mixing efficiency, and finite-rate chemistry are also included. The SUNDIALS code is used to solve the stiff ordinary differential equations for combustion flow and the nonstiff ones for coolant flow individually, which are thermally coupled and iteratively solved to obtain the variables of the flowfields and the performance of the combustor with the consideration of the effect of regenerative cooling. Examples of hydrogen cooled scramjets were simulated under Mach 7.7 with strut injectors. Compared to the combustor without regenerative cooling, the differences on ignition delay, mixing efficiency, and engine performance were observed in a regeneratively cooled scramjet.
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