Thermodynamic performance analysis of a high-Mach low-carbon turbine engine system with integrated precooling and power generation system

To address the significant performance degradation of turbojet engines at high Mach numbers, this study proposes a precooled power generation engine system employing a dual-fuel combination of liquid ammonia and kerosene. A precooler is positioned upstream of the compressor to cool the incoming high-temperature air, while a thermo-ammonia turbine is integrated between the precooler stages. This configuration not only supplies electrical power but also reduces the temperature of the precooling fuel, thereby realizing a two-stage precooling concept and enhancing the overall cooling effect. Modeling and system calculations indicate that the proposed system increases the maximum flight Mach number from 3.2 of conventional turbojet engines to 4.6, achieves a precooling intensity 1.58 times that of traditional precooled engines, and generates up to 1.46 × 10⁷ W of electric power. Overall, the system demonstrates strong potential for improving propulsion performance while significantly reducing carbon emissions.