Numerical Simulation On Flow And Heat Transfer Characteristics Of Kerosene Flowing In A Pipe Under High Heat Flux

Kerosene not only the fuel of the scramjet,and is also its cooling agent, it’s cooling performanceis very important. Especially when the Mach number increase（sMa>5）, the cooling demand increasesgreatly,and fuel cooling capacity determines the ability of the flight. So the research of kerosene flowand heat transfer characteristics is significant.In this paper,we research on the two-phase flow ofgas-liquid phase transition of Daqing RP-3aviation kerosene in a pipe under the conditions of highheat flux,and investigate the flow and heat transfer characteristics of kerosene in active cooling panelsof hypersonic vehicle.Firstly,this paper discusses the thermophysical properties of kerosene,and calculateshermophysical properties of Daqing RP-3aviation kerosene by NIST Supertrapp software with threecomponents alternative model. Do simple assume that phase transition of Daqing RP-3aviationkerosene in a pipe.The validation of the model,based on experimental result of heat transfer in astainless steel tube for kerosene is presented.Secondly,numerical simulate the two-phase flow of gas-liquid phase transition of Daqing RP-3aviation kerosene in a pipe at high heat flow.We got the the relationships between cooling effect ofthis kerosene and different inlet velocity、inlet temperature and pressure. The results revealed thatunder the condition of the same heat flux,with the inlet temperature of kerosene increased,walltemperature and wall average temperature are reduced,wall average heat transfer coefficientincreases,beneficial to the heat transfer.;under the condition of the low heat flux,the influence of theinlet temperature on the pressure loss is not big,but with the increase of heat flux,the inlet temperaturehigher,the pressure loss more;under the condition of the same heat flux,the higher the inlet pressure ofkerosene,the worse of the heat transfer,but the higher the inlet pressure of kerosene,the smaller thepressure loss;along with the increase of the inlet speed,wall temperature will decreases,it is good forheat transfer.Finally,we did the numerical simulation on the cooling effect of the combustor panel forregenerative cooling of hypersonic scramjet engine,analyzed the cooling effect of the regenerativecooling by different flow rate of cooling medium and the sizes of channels. The results revealed thatwith the bigger the inlet mass flow of kerosene,the more beneficial to the heat transfer,but thecontribution of the cooling effect by increased inlet mass flow of kerosene reduced gradually; And thebigger the inlet mass flow of kerosene,the bigger total pressure loss in the cooling channels. Withincrease the height and width of the cooling channels,cooling performance of cooling panel will be worse,but this kind of effect will abate gradually; With increase the height and width of the coolingchannels,the total pressure loss in the cooling channels reduced sharply. Different way of the keroseneflow has effect on the heat transfer performance of the cooling panel,especially for the temperaturedistribution on the wall,so it has a significant positive effect of equalizing the temperature distributionto arrange the cooling channels in cooling panel reasonably.