The Supersonic Combustion Ramjet Combustor Regeneratively Cooled Research

Regenerative cooling technology is one of the key technologies to thermally protect scramjet chamber. To the author's knowledge, no domestic reports were found about this technology applied to scramjet. So there is important theory significance and engineering merit to study regeneratively cooled scramjet in depth.In the first chapter ,the thermal environment of scramjet and the inevitablility of regeneratively cooled scramjet,the history and state of art of the studies on regeneratively cooled scramjet and regenerative cooling technology were described comprehensively. Through this material one could setup an overall impression of the study content and the study method.In order to investigate the basic heat transfer characteristics of regeneratively cooled scramjet, in the second chapter, one dimensional heat transfer model of regeneratively cooled scramjet was developed. In this model, N-R correlations were used to describe hot gas-side and coolant-side convection heat transfer. Simple model of gas properties was also used. The parametric studies on the effect of liner material, liner thickness and coolant mass flow rate were conducted.In the third chapter, the reference enthalpy method was used to describe the convection heat transfer from gas to wall. Basing on the N-R correlation, several correlations were added to consider the effects on heat transfer coefficient, including the entrance effect, cooling channel roughness, fluid property variation and so on. Thermal balance method was used to get the discrete equation for the two dimensional conduction of wall. One set of analytical expressions for domestic aviation kerosene properties was given basing on the composition measurement result. Thus the thermal evaluation tool was set up .Then one case was compared with other test data or computational data. Finally,the application areas were compared between the methods in this chapter and the second chapter.In the fourth chapter, the thermal evaluation tool was applied to analyze the cold flow and hot flow scramjet experiments, in which the coolant was water and kerosene. The calculational data was compared with the experimental data.In the fifth chapter, the thermal evaluation tool was applied to parametric studies on the effects of material choice (liner material, close-out material and coat material) and geometry (liner thickness, fin thickness, cooling channel width and height).Through the studies on the regeneratively cooled scramjet structure of tomorrow's advanced propulsion system of this paper, one thermal evaluation tool was developed. This dissertation provided the necessary means for the design of regenerative cooling channels of the scramjet.