In order to establish assessment and optimization method of combustor regenerative cooling system, one-dimensional heat transfer analysis coupling the supersonic combustor flow, the coolant flow and the cooling wall was developed. Without pressure data obtained from experiments and assumption for the distribution of total temperature and heat release, the flow properties of the combustor were obtained by directly solving the mass, momentum and energy differential equations with fuel mixing and reaction modeling. The flow and heat transfer properties of the coolant at varied states were solved and coupled with the combustor flow by calculating the heat conduction through the cooling wall. The thermal and catalytic cracking of the aviation kerosene were considered in the present model and their effects on the cooling were studied. It is found that at flow conditions of Mach 6 flight, the cracking effect on the cooling is obvious in the downstream half part of the combustor and the hot-wall temperature is further reduced due to the endothermicity of the kerosene cracking. Compared with thermal cracking, catalytic cracking increases the cooling effectiveness even further.
; 陈立红
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