The supersonic combustion flow with transverse hydrogen jet in scramjet configuration with and without wedge structure is numerically studied. The characteristics of flow field structures and parameters under different inlet Mach numbers in the combustion chamber with wedge structure or not are analyzed. The combustion flow is numerically simulated with Reynold-averaged multi-component N-S equations solved, based on the finite volume method.And the properties of shock structure, jet penetration depth, combustion surface, combustion efficiency and total pressure recovery coefficient are carefully compared under different inlet Mach number. The result shows that whether wedge structure exists or not, the pressure of the flow field behind the jet decreases with the increase of the inlet Mach number, as well as the decreases of the penetration depth of hydrogen jet. There is little effect of wedge structure on jet penetration height. Compared with wedge-free structure, the wedge structure can alleviate the sensitivity of the flow field in the combustor to the change of inlet Mach number and make the combustion more stable. Under the same inlet Mach number, the applicability of the combustor is promoted by employing the wedge-cavity structure, and the shock igniting is markedly enhanced by the wedge with acceptable reduce of the total pressure recovery coefficient, which can increase the inlet Mach number range of this kind of engine.