A parametric three-dimensional study of combustion modes and thrust performance in rotating detonation engine with aerospike nozzle.

This article focuses on a three-dimensional numerical investigation of rotating detonation engines (RDEs) equipped with back aerospike nozzles, analyzing how inflow total pressure, nozzle throat ratio, and combustion chamber width affect combustion modes and thrust performance. The study finds that decreasing the nozzle throat ratio induces a transition from stable single-wave detonation to unstable multi-wave modes due to reflected shock waves compressing the detonation wave and generating hotspots near the inlet. Increasing inflow pressure and chamber width tends to stabilize detonation waves by raising chamber pressure and preventing upstream shock wave propagation, while also enhancing thrust primarily through increased mass flow rates; however, specific impulse remains relatively unchanged. The research highlights a nonlinear relationship between throat ratio and thrust, where reduced throat ratios initially increase chamber pressure and specific impulse but eventually lead to unstable combustion and decreased performance. These findings contribute to optimizing RDE design by clarifying the interplay between nozzle geometry, inflow conditions, and combustion stability.