Matching mechanism of a novel variable cycle propulsion concept with hydrogen intercooling

Supersonic aircraft capable of operating across wide speed and altitude ranges have garnered increasing attention in recent years, owing to their extensive application potential. However, current propulsion cycle schemes face notable challenges in meeting the performance demands of supersonic aircraft, primarily due to their inability to reconcile the conflicting cycle parameter requirements of high-speed and low-speed operations. This study proposes a novel variable cycle propulsion concept with hydrogen intercooling, develops a performance simulation model, and analysis the matching mechanism of this novel thermal cycle. The propulsion cycle combines the strengths of both variable cycle and precooled technologies, achieving high efficiency and sufficient thrust across a wide speed range from 0 to Mach 3.5. The design of hydrogen intercooling also addresses the critical issue of insufficient heat sink capacity in current turbine-based cycle engine and ensures the coolant is completed consumed during combustion. Results indicate that, compared with conventional variable cycle schemes, the proposed propulsion cycle increases thrust by 38.16 %, reduces specific fuel consumption by 47.69 %, and extends the flight speed range from Mach 2.8 to Mach 3.5. This novel propulsion concept provides a promising approach to enhancing energy utilization efficiency and effectively supports the application and deployment of supersonic aircraft.