The potential benefits of reheat burner placed between turbine stages for propulsion system have been recognized for nearly a century. Compared to the conventional non-reheat engines, the turbine inter-guide-vane burner (TIB) engines by using jet-swirl flow scheme (high-G loading) are shown to have a higher specific thrust with no or only small increase in thrust specif-ic fuel consumption. But, it is a known fact that the G loading in the circumferential cavity is inversely proportional to the radius of the circumferential cavity. If one needs to scale this configuration for a larger spool of turbine components, the effectiveness of the high G operation and obtained benefits on flame speed will reduce and hence the performance will de-grade. Hence to make a universal TIB, an alternate approach was proposed using a trapped vortex cavity to replace the jet-swirl flow combustion to enhance mixing rates via a jet-vortex flow in the cavity, followed by further mixing of the free stream air through the guide vane with a notch. The various structures of radial vane cavity are focused on in this study to research effect of this cavity structure on performance of turbine inter-vane burner based on jet-vortex flow, such as straight cavity; hypsokinesis cavity; fore-rake cavity; circle cavity; half cavity, and to cover the shortage of co-relational research in the field of turbine inter-vane burner. And the Scale-Adaptive Simulation (SAS) turbulence model is used in the simulation process. Finally, compared with the other models, various performance parameters in term of combustion efficiency (η), total pressure loss (dp/p), pollutant emissions of CO, and unburned hydrocarbons (UHC) for the model-3 is much better, and the application of turbine inter-vane burner technology based on jet-vortex flow in gas turbine engine is the effective solution to these bottleneck problems traditional for traditional civilian aero-engine.