Description: Traditional thermal management methods used in rocket combustion systems are not readily applicable in the RDRE framework due to the higher cooling load demands from the same propellant feed system. Therefore, significant research and development efforts are essential for RDRE thermal management. Specifically, heat-flux loads, as obtained through traditional calorimeter data, face challenges in the RDRE framework due to axial variations in reactant stratification, detonation wave riding near the outer wall, and high periodic heat-fluxes. The high heat-flux density also presents challenges in providing optical access for diagnostic evaluations of various unsteady interactions in RDREs, essential for a physics-based understanding through the use of optical diagnostics. The proposed work here aims to understand these complicated questions with a suite of temporally and spatially resolved diagnostics and the experience to make these detailed measurements in such harsh environments.

Benefits: NASA has identified the RDRE as a technology of interest for its in-space propulsion applications such as orbital transfer or planetary lander engines. A full understanding of Heat transfer is required to minimize the cooling process to thus carry more payload, go faster, or travel further. The heat transfer experimental framework can be transferred to NASA for ground test facilities to quantify the cooling and material requirements for their systems. Heat transfer data and material response for understanding the requirements to achieve long duration run time and if designs of regen cooling are sufficient for these harsh environments.