Rotating detonation engines (RDEs) have garnered substantial attention as an emerging technology with applications to aerospace propulsion and energy generation due to their high-power density. Significant research and development have improved the operability and performance of RDEs, but relatively few studies have investigated the problems associated with integrating the combustor into an airframe. The U.S. Air Force Research Laboratory has identified this gap and initiated efforts to address the need.
This presentation will cover the following:
- Various efforts to develop inlet design procedures specific to RDE propulsions systems
- An assessment of inlet-combustor compatibility
- Various combustor development activities with an integration focus
- Areas for future research.