Overall performance analysis of pulse detonation turbofan engine

Abstract A performance model was developed to evaluate the pulse detonation turbofan engine (PDTFE). The influence of cycle parameters on the pressure ratio of the pulse detonation combustor (PDC) and the design point performance of the PDTFE were analysed. Using a selected set of design point parameters, the off-design performance was calculated. Results show that, compared to traditional turbofan engines with isobaric combustion, the PDTFE provides substantially higher specific thrust and lower specific fuel consumption. However, as the total pressure ratio of the compressor increases, the PDC pressure ratio decreases, leading to a reduction in the advantages of specific thrust and specific fuel consumption for the PDTFE. When maintaining the same total pressure ratio of the compressor, the PDTFE demonstrates a 21.6 % increase in specific thrust and an 8.3 % decrease in specific fuel consumption relative to traditional turbofan engines. Under cruise conditions at 8 km altitude and Mach 0–1.5, specific thrust improves by 23 %–32.5 % and specific fuel consumption drops by 2 %–8 % compared to a traditional turbofan with the same design point parameters.