The aviation market has seen a drastic rise in past decades, and is projected to follow a similar trend in the coming years. Stricter regulations and ambitious targets have been framed to effectively curtail the rise in emissions due to this surge in aviation. A multi-fuel blended wing body aircraft is being developed in TUDelft, with the goal of drastically reducing aircraft emissions. To this end, a dual-combustor configuration, which operates with a main combustion chamber and an inter-turbine burner has been proposed. The exhaust gas from the main combustion chamber passes through the high pressure turbine and then proceeds to the inter-turbine burner. It is important to accurately model the evolution of exhaust gas species, from the main combustion chamber through the high-pressure turbine, since this constitutes the species concentration at the inlet of the inter-turbine burner. This, in turn, can have impacts on its performance too. Therefore, this thesis aims to do a detailed parametric analysis to study the individual impact of the operating conditions on the chemical kinetics after the main combustor. The operating temperature has been identified as the most significant parameter that would have drastic impacts on the way emissions evolve after the combustor. The predictions of Turbine Inlet Temperatures for future aircraft have shown only a steady increase. Although the assumption of frozen chemistry after the combustor may have been valid for older engines, the same does not hold as good for futuristic configurations. Newer and different engine architectures like the hybrid engine, which are designed to operate on high cycle temperatures and pressures, cannot ignore the consequence of change in emissions after the combustor in order to retain accuracy in estimations.