宽范围超临界二氧化碳布雷顿循环高超声速发动机热防护和发电-体化研究

The escalating electrical loads of on-board equipment and the increased performance requirements of thermal protection systems of hypersonic vehicles have become the key bottlenecks restricting their development. To reduce fuel consumption under high Mach number conditions and improve the thermal protection performance of aircraft，this article proposes a two-stage expansion cycle to study the influences of split point position，inlet pressure of turbine 1，and inlet pressure of turbine 2 on fuel consumption. To improve the power generation performance of the low Mach number operating system，a simple reheating supercritical carbon dioxide （S-CO₂）Brayton cycle is adopted. The influences of compressor inlet temperature，turbine inlet pressure，and fuel outlet temperature on the net power and efficiency of the system cycle are studied. The fuel consumption is initially optimized using the Whale Optimization Algorithm（WOA），followed by a multi-objective optimization considering system cycle efficiency，cycle net work power output，and system mass. The results demonstrate that the fuel consumption at Mach 6~8 is reduced by 15.19%~17.59% compared to the simple Brayton cycle. Under equivalent cycle efficiency and net work power output conditions，the system weight utilizing Triply Periodic Minimal Surfaces（TPMS）as regenerators and coolers is 60%~70% of that using Printed Circuit Heat Exchangers （PCHE）. By implementing bypass configurations for turbine 1 and regenerators，an integrated wide-range SCO₂ Brayton cycle system was developed，achieving combined thermal protection and power generation for hypersonic aircraft engines.