一种适用于二冲程航空重油活塞发动机的复合动力系统构型及其性能影响因素分析

In response to high power density and low fuel consumption, an aviation piston-turbine hybrid power system configuration was proposed, wherein the piston subsystem adopted a two stroke aviation heavy oil piston engine with horizontally opposed cylinders, and the turbine subsystem consisted of a burner and a turbocharger. Based on the GT-POWER platform, the accuracy of the simulation model was verified using a comparative study of cylinder pressure. The effects of turbocharger efficiency, turbine efficiency, reheating fuel flow rate, and altitude on the performance of hybrid power system were studied, and the system performance was evaluated based on brake specific fuel consumption and output torque. The research results showed that the hybrid system can increase the output torque by about 30% compared with the aviation piston engine at the limit state. The torque gain generated by a 10% increase in compressor efficiency was greater than the torque gain generated by a 10% increase in turbine efficiency. When the reheating fuel flow rate in front of the turbine was 0.2 g/s, the exhaust temperature can be increased by about 150 K, and the output torque at all operating points can be increased by more than 20%. Therefore, reheating in front of a turbine is an effective means to improve the performance of an aviation piston-turbine hybrid system.