Structural Characteristic Of Transverse Kerosene Jet In The Cold Scramjet Combustor

Scramjet combustor,as the core component of hypersonic populsion technology,improving its effective mixing between fuel and air is the key to advance the combustion efficiency in the cold supersonic cross flow.Based on developed Computational Fluid Dynamics method including discrete phase model of Euler Lagrange method,improved K-H & R-T model,SST k-? turbulence model and surface evaporation model,studies have already addressed the injection,atomization and mixing between incoming flow and kerosene in cold supersonic flow with taking the combustion chamber of a cold scramjet combustor for research object.Studies are summarized as follow:1)Studies introduce the numerical simulation method and the corresponding control equation in detail,such as volume tracking and interface tracking method for multiphase flow,discrete phase model of Euler Lagrange method,droplets turbulence model,atomization and evaporation model.2)In the cold supersonic flow,the injection parameters including injection diameter,spray angle and injection pressure have more obvious impact on the injection characteristic of transverse kerosene single jet,such as penetration height of kerosene jet,span expansion area,angle of shock wave,total pressure loss of crossflow and sauter mean diameter(SMD)distribution of kerosene droplets.The simulation results show that with injection diameter,spray angle and injection pressure getting larger,the penetration height of kerosene jet,span expansion area,angle of shock wave and total pressure loss of the crossflow increased.3)In the cold supersonic flow,the injection characteristic of transverse kerosene double jets comprising penetration height of kerosene jet,span expansion area,angle of shock wave,total pressure loss and sauter mean diameter(SMD)distribution of kerosene droplets were studied numerically.The result demonstrated that the spanwise assembled double injectors significantly increased the spanwise expansion,penetration height of the kerosene jet,angle of shock wave and total pressure loss of crossflow in comparison to the injection of the single injector.Besides,compared with the single injector,the streamwise assembled double injectors were favorable to obviously increase the penetration height of the kerosene jet and pressure loss,but it has made no great difference to the span expansion area.The calculation predictions are compared against the reported experimental measurements and literatures with good qualitative agreement.The simulation results obtained in this study can provide some theoretical basis for deep understanding the underlying mechanism of kerosene atomization in cold supersonic flow and scramjet design improvement,and also provide better practical significance for improving effective kerosene combustion and optimizing flame stabilization device.