Integration of Film Cooling in a Micro Rotating Detonation Combustor

Rotating Detonation Combustors (RDCs) have recently garnered significant attention in aero combustion research due to their potential efficiency advantages over conventional deflagration-based systems. Micro-scale RDCs in particular have proven invaluable for the detailed scientific investigation of detonation dynamics. They offer reduced manufacturing costs and standardized geometries that facilitate systematic exploration of detonation processes. However, integrating RDCs into practical gas turbine systems remains challenging, with thermal management emerging as a critical issue due to the extreme heat flux generated during detonation. Effective cooling strategies are essential to prevent structural degradation and ensure sustained operation. To address this, recent research efforts have focused on adapting conventional cooling approaches for these systems. This study details the design and development of a micro RDC test facility tailored to investigate the effects of film cooling in an oxygen ethylene fueled micro rotating detonation combustor. The primary aim is to evaluate how film cooling influences thermal loads on the outer combustor walls, while also examining its impact on detonation wave characteristics, including wave stability, propagation speed, and overall combustion performance. The cooled test campaign confirms the feasibility of implementing film cooling in this micro-RDC geometry across a wide range of operating conditions. Stable detonations were consistently achieved, and a significant reduction in wall temperature was observed in regions near the cooling holes, demonstrating the effectiveness of the film cooling strategy in mitigating thermal loads without compromising detonation stability or performance.