航空活塞发动机串联二级增压压比分配研究

针对某款航空活塞发动机建立仿真建模，并通过实验验证了模型的准确性和适用性；根据匹配要求，进行了增压器选型分析。考虑不同飞行高度中冷器效率和各部分流动阻力变化的前提下，以增压压气机耗功最小为优化目标研究了在全飞行高度运行工况下不同压比分配对发动机增压性能的影响，探究了最适压比分配规律，以此为依据总结出一套基于实验制定二级增压压比分配方案的方法，使二级增压器能全工况运行在高效率区且保持7%以上安全裕度，为基于安全性的二级涡轮增压航空活塞发动机的研制奠定了基础。 

Study of compression ratio distribution in two-stage series turbocharged aircraft piston engine

A calibrated simulation model was created in this research and the accuracy and applicability was verified by experiment. This model was used to match the appropriate turbochargers and explore how the diverse pressure ratio distribution affects the engine performance on the whole operating range considering the efficacy of the intercooler and pressure loss in inlet. Based on the objective of minimizing the energy consumption of turbocharging compressors, series of theories were revealed about how to distribute the pressure ratio between two turbochargers, and a matching method was got to optimize the pressure ratio distribution on a certain two-stage turbocharged aircraft piston engine by virtue of research. Results showed the turbochargers had high efficiency under all working condition and kept 7% away from the dangerous margin via the method. This also provided a foundation for further study on the safety of the two-stage turbocharged aircraft piston engine at service ceiling.