Ajay Agrawal
University of Alabama, Tuscaloosa
This project will develop an integrated system for rocket applications based on a hybrid configuration using combined features of an axial rotating detonation combustor (RDC) and a radial (or disk) RDC to dramatically reduce weight, and improve performance and operational simplicity/flexibility of the space flight hardware. Project goal is to gradually decrease the flow area in the radial direction and strategically turn the radial inflow towards an axial flow integrating the combustor naturally with the downstream nozzle, providing high performance of the combined system. The flow cross-section is varied to weaken the oblique shock wave attached to the rotating detonation wave. This geometric design of the RDC flow channel is also intended to reduce the pressure and velocity fluctuations that can lead to detrimental thrust variations or engine failure.
The overall effort consists of : (1) engine cycle studies to establish the key design parameters, (2) computational fluid dynamic (CFD) analysis using well-established software codes and research capabilities for detonation simulations at the Naval Research Lab (NRL), and (3) hardware design and development, instrumentation, experimental demonstration/validation, and refinements using experimental capabilities including high-speed intrusive probes and optical diagnostics. The compact design combined with expected high performance of the coupled hybrid RDC system would make space travel and exploration more effective, affordable, and sustainable.