涡轮前温度对混排涡扇发动机全速域性能影响研究

The continuous increase in turbine inlet temperature can enhance the specific thrust of the aero engine during takeoff，but it also has complex adverse effects on the subsonic cruise and supersonic comprehensive performance of the engine. In order to deeply analyze the impact mechanism of turbine inlet temperature on the comprehensive performance across the entire speed range，and to provide guidance and reference for the overall design of future advanced supersonic engines，this paper establishes a comprehensive turbofan engine design optimization and matching model across the entire speed range for a typical mixed exhaust turbofan engine configuration，considering the limitations of blade endurance temperature and maximum combustion equivalence ratio. The model analyzes the impact of increased turbine inlet temperature on the matching parameters of turbofan engine components，key channel dimensions，and comprehensive performance across the entire speed range. The results show that under the constraints of the traditional mixed exhaust turbofan engine configuration，an increase in the design value of turbine inlet temperature can improve the takeoff specific thrust and super-cruise speed to a certain extent，but it also leads to a decrease in flow capacity. For every 100 K increase in turbine inlet temperature，the subsonic cruise specific fuel consumption increases by nearly 2%，the maximum super-cruise Mach number increases by less than 0.08，and the maximum flight Mach number actually decreases by about 0.02. On the premise of the engine configuration remaining unchanged，as the turbine inlet temperature continues to rise，its marginal benefits become increasingly limited，and the costs become more significant. The insufficient flow capacity of the mixed exhaust turbofan engine at low corrected rotational speeds is a key factor limiting the improvement of its comprehensive performance.