Skin friction reduction for boundary layer combustion in a scramjet engine
HE Xin1, XUE Rui1, ZHENG Xing1, ZHANG Qian1, GONG Jianliang2
1. State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi'an Jiaotong University, Xi'an 710049, China; 2. Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Abstract：The skin friction characteristics for boundary layer combustion in a scramjet engine were studied numerically by analyzing the effect of adding a boundary layer combustion device and for changes in the scramjet exhaust nozzle lower wall inclination angle. The combustion was modeled using a hydrogen-air kinetics model consisting of 9 species and 27 reaction steps with the flow modeled. The turbulence was modeled using the four-equation Transition SST (shear stress transport) turbulence model which takes account the boundary layer transition to accurately predict the hydrogen combustion in the boundary layer with the hydrogen injected from the boundary layer combustion device. The investigation of the effects of various exhaust nozzle lower wall inclination angles shows that the flow expansion inhibits boundary layer combustion in the combustion chamber while dramatically reducing the skin friction in the exhaust nozzle. In contrast, a contracting exhaust nozzle enhances the boundary layer combustion in the combustion chamber while increasing the flow resistance. However, the boundary layer flame is extinguished before it propagates into the nozzle section, which further increases the skin friction. Thus, if the boundary layer combustion flame can be spread into and stabilized in the nozzle section, the scramjet with a contraction profile will exhibit superior skin friction reductions.
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2022, Vol. 62 
