Numerical Study On Heat Transfer Characteristics Of Supercritical Aviation Kerosene At Ultrahigh Heat Flux

With the continuous improvement of the Mach number of the hypersonic vehicle,the flying environment of the aircraft at high altitude or even near space is getting worse,which puts forward higher requirements for the active cooling of the aircraft.Liquid rocket engine and scramjet engine has been used as a hotspot of high-supersonic cruise missiles,hypersonic aircraft,space planes and other popular power devices,as the world’s research hotspot.Active recirculation cooling As a cooling system for such engines,it is possible to adapt to a more harsh working environment where the fuel of the engine also acts as a coolant and the flow heat transfer characteristics in the cooling channel directly affect the engine cooling System performance.Therefore,it is of great significance to study the change of thermal kerosene for ultrahigh pressure and super high heat flow to study the cooling system of transcendental ramjet.In this paper,supercritical aviation kerosene(Daqing RP-3)is used as the research object,and the numerical simulation method is used to study the flow heat transfer characteristics in horizontal circular and serpentine channels.First,under the condition of high pressure aviation kerosene(Daqing RP-3 type)as the research object.The mechanical properties of aviation kerosene were studied by NIST property calculation software,and the thermophysical properties of aviation kerosene were obtained.The numerical simulation results of aerosol kerosene were carried out by using the numerical simulation results of the aerosol properties of aviation kerosene.The accuracy of the calculated kerosene was calculated and the feasibility of the numerical method was verified.Secondly,the numerical simulation method and the supercritical aviation kerosene property fit formula were used to calculate the flow phenomena of aviation kerosene at different pressures and temperatures in horizontal straight pipe with length of 500 mm and diameter of 1.8mm.The key factors of different flow The influencing factors of flow fluxes in the cooling channel are studied.The key factors include inlet mass flow,wall heat flow and working pressure.The first calculation of pressure up to 20 MPa,wall heat flow of 15 MW / m2 calculation conditions.It can be seen that the inlet mass flow and wall heat flow have a great influence on the wall temperature,the kerosene temperature and the channel heat transfer coefficient,and the working pressure has little effect on the temperature field and velocity field.Finally,in order to achieve better heat transfer effect,this paper designed the serpentine enhanced heat transfer channel and carried out the relevant numerical simulation study.Considering the influence of centrifugal force on the kerosene flow in the channel,the influence of inlet mass flow and outlet pressure on flow heat transfer was discussed.Compared with the straight pipe channel,the serpentine enhanced heat transfer channel will produce different vortex structures in the process of kerosene flow,destroy the thermal boundary layer of the channel wall,increase the heat transfer in the channel,and the numerical results show that the serpentine channel has more High heat transfer coefficient,but there is a large drawback of pressure loss.