Design and experimental investigation of a pulse detonation gas-driven distributed propulsion prototype

To investigate the feasibility of the pulse detonation gas-driven distributed propulsion (PDGDDP) system at both the conceptual and technical levels, a prototype experimental platform was developed and tested. A multi-design-parameter optimization model was established by integrating the differential evolution algorithm with the previously developed performance evaluation model, and the optimal design parameters of the PDGDDP system were thereby determined. Based on these results, single-channel and dual-channel prototypes were built and experimentally studied. The results showed that the PDGDDP system achieved a predicted total thrust of 10,324 N and a specific fuel consumption of 0.03059 kg/(N·h) under the optimal design parameter combination, with a 36.8%-62.3% reduction in specific fuel consumption relative to conventional turbofan engines at an equivalent thrust level. The single-channel PDGDDP prototype operated stably at ignition frequencies (f_PDC) of 10–25 Hz, with successful detonation wave generation and net thrust production. The thrust increased with f_PDC and reached an average of 338.6 N at the design-point frequency of 25 Hz. Nevertheless, the actual performance was significantly lower than the ideal prediction, mainly due to the marked reduction in turbine efficiency under detonation gas inflow conditions. Compared with the ideal case, the actual turbine efficiency was reduced by 46.7%. Both channels of the dual-channel prototype sustained stable detonation combustion under different operating conditions, confirming the feasibility of stable and coordinated operation of multiple distributed propulsors in the PDGDDP system. These results demonstrate the feasibility of the PDGDDP concept and provide experimental support for its further development.