Shock/boundary layer interactions (SBLI) are an unavoidable physical phenomena having significant consequences in high-speed flights and supersonic flows. Among the various categories of SBLI, transverse sonic injections into a turbulent flow involves blockage of the incoming supersonic flow by the injected fluid. This results in formation of strong bow shocks and wake regions. The adverse pressure gradients leads to boundary layer separation and shock turbulent boundary layer interactions (STBLIs). Such shock-shock interactions in the turbulent boundary layer are the primary focus of this work. The results of an Implicit Large Eddy Simulations (ILES) of SBLI are presented here to provide insights into their behaviour using the OpenSBLI numerical solver on a GPU cluster. The simulations are performed on a 3D flat plate with a freestream Mach number of 2.0 and an inflow Reynolds number of 500 based on the inflow momentum thickness (θ). The injection studies revealed various shockshock, shock-turbulence and shock-vortex interactions. This enhances the mixing of the flow which is desired for SCRAMJET like applications. These interactions form regions of higher turbulence intensity (vortices) interacting with the boundary layer.