With the ever-growing demand for power generation to support the world economy and electric transportation needs, efficient gas turbine power cycles need to be investigated to match the anticipated high demands of the future. Decarbonization efforts around the world to achieve Net Carbon Zero by 2050 have also brought many new challenges for the development of these systems due to the unique constraints imposed by less carbon-intensive fuels. In this effort to increase the efficiency and performance of such gas turbine power cycles, pressure gain combustion (PGC) has gained significant interest. The potential for an increase in the thermodynamic efficiency over the constant-pressure Brayton Cycle has made detonation combustors, a type of PGC, an attractive alternative to traditional deflagration-type combustors. Since Rotating Detonation Combustors (RDC) can provide a quasi-steady mode of operation when compared to Pulse Detonation Combustors (PDC), research has been triggered to integrate RDC with power-generating gas turbines. However, the presence of subsonic and supersonic flow fields which are generated due to the shock waves that stem from the detonation wave front and the highly non-uniform temperature and velocity profiles may cause a depreciation in the turbine performance. The current study seeks to investigate the challenges of integrating the RDC with nozzle guide vanes (NGV) of an industrial, can-annular gas turbine and attempts to understand the major contributors that impact efficiency and identify the key areas of optimization that need to be considered for maximizing performance. In order to compare the results with an F class gas turbine engine condition, a geometric model of RDC developed by the Air Force Research Laboratory (AFRL) was scaled using a linear mass flow to area relationship, aiming to achieve a higher flow rate. The RDC was integrated with the NGVs through a non-optimized straight duct-type geometry with a diffuser cone. 3-Dimensional Numerical analyses were performed to investigate sources of total pressure loss and to understand the unsteady effects of RDC which contribute towards the deterioration of performance. The entropy generation at different regions of interest was calculated to identify the major irreversibility's in the system. Finally, total pressure and temperature distribution along the radial direction at the exit of the transitional duct is presented to understand the various constraints imposed by the RDC when integrating with an Industrial gas turbine engine NGV. / Master of Science / In recent years, power generation has become more challenging and complex due to the ever-growing demand for running a developed or developing economy. With electric transportation becoming more accessible and affordable for the general public, an increase in the demand for power generation is expected in the future. Coupled with this is the ambition of every nation to move toward NetCarbonZero by 2050, to reduce emissions as well as move towards a more sustainable future for the next generations. One of the primary sources of power generation in modern-day industry comes from industrial gas turbine engines, due to their reliability in providing electricity to ensure grid stability as well as maintaining near-zero emission levels. But after decades of research and advancements, the constant pressure deflagration combustion process occurring in the combustors of these gas turbine engines which follow a Brayton cycle has reached to the stage where only incremental gains can now be achieved. However, detonation combustion, which is thermodynamically more efficient because of the constant volume combustion process, modifying the Brayton cycle to a Humphery cycle. Coupled with the possibility of a pressure gain type of combustion system, investigation has been triggered in recent years by many researchers and industry for matching the increase in power generation demands with detonation combustion. In this study, a Rotating Detonations Combustor (RDC), a type of continuous detonation wave propagating system is numerically investigated using a Simcenter Star CCM+ commercial CFD solver. A scaling approach, which has been pervious implemented for can-type combustor systems was modified and used to scale an RDC geometry to match the industrial gas turbine operating condition. The scaled RDC geometry was modeled with a transitional duct and a pair of Nozzle Guide Vanes (NGV) and 3D reacting numerical analysis was conducted to understand the pressure loss mechanism at various regions. These results should help future designers and researchers in conducting several design studies as well as implementing optimization methods for increasing the performance of this novel combustor technology.