Pressure loss across a combustor in a gas turbine reduces thermal efficiency and increases specific fuel consumption. Theoretically, any pressure gain across the combustor results in higher thermal efficiency and lower specific fuel consumption. This work aims to obtain ‘time-averaged pressure rise across the combustor by using shock-flame interaction’. Multiple shock flame interaction increases the chemical heat release rate by two orders of magnitude. In this study, an impulsive heat addition for 30 microseconds with different heat release rates (10,30 and 100) is applied to a spherical zone within the primary zone of the combustor after a quasi-steady URANS combustion and the results are evaluated. A further study, the experimental part, will be based on shock flame interaction with different strengths of shocks. Inlet and outlet total pressures will be measured via high-pressure and high-temperature pressure transducers. Any pressure gain combustion can save billions of USD as gas turbines consume 13.9% of the total energy consumption.