An integrated combustor-turbine module: aerodynamic and thermal analysis under uniform and swirling flows

This study systematically investigates a novel integrated combustor-turbine module (ICTM), focusing on its aerothermal characteristics and cooling performance under diverse inlet conditions. The ICTM design merges the combustor flame tube with first-stage turbine vanes, creating an independent aerodynamic and cooling unit. Utilizing computational fluid dynamics (CFD) simulations, the study evaluates the module’s performance across uniform, positive swirl, and negative swirl inlet conditions. Results show that the ICTM achieves a 28.9% reduction in total pressure loss coefficient compared to conventional designs, highlighting its high aerodynamic efficiency. Furthermore, the ICTM demonstrates significantly lower heat transfer coefficients, with a 13% decrease in surface-averaged values and a 53% reduction in peak values. The cooling design of the ICTM also shows enhanced potential, requiring less coolant flow and featuring simplified film cooling configurations. Notably, the ICTM maintains superior aerothermal performance under non-uniform swirling inlet conditions, outperforming conventional designs in both aerodynamic efficiency and heat transfer characteristics. This research establishes the ICTM as a promising design paradigm for next-generation heavy-duty gas turbines, offering valuable insights for advanced engine systems.