Efficient fuel/air mixing and combustion are difficult to achieve in supersonic flows. Transverse fuel injection from combustor walls is commonly used in Scramjet (supersonic combustion ramjet) design. The present study proposes an approach to enhance supersonic combustion under those conditions. Based on the specific jet-to-crossflow flow structures, it is proposed to connect the upstream region and downstream region of fuel injection slot through a channel. The higher pressure upstream of the slot drives part of the fluid flow into downstream regions and a self-throttling is established. Numerical method is used to validate the concept for a model combustor applying RANS (Reynolds-Averaged Navier-Stokes) approach. A compressibility modification k - epsilon turbulence model is used which combines the dilatational compressibility effect and shock unsteadiness effect. The modified turbulence model is found to be able to capture the complex flow structures with good accuracy. Five operating conditions of jet-to-crossflow pressure ratio are studied for both nonreactive and reactive flows. The results show that the self-throttling changes the flow fields a lot, and affects the separation region and interactions of the reflection shock with mixing layers downstream the injection slot. Its effects on mixing and combustion efficiency are analysed for five different cases. The results demonstrate that self-throttling approach can increase the combustion efficiency with relative low injection pressure where the reflection shock goes downstream the injection slot. At the same time, more total pressure loss is observed. The combustion enhancement is more significant with relative low injection pressure. The self-throttling method has potentials for further studies. Copyright (C) 2015, Hydrogen Energy Publications, LLC. Published by Elsevier Ltd. All rights reserved.