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  

Scheme and performance analysis of a hybrid power system for two stroke aviation heavy fuel piston engine

作　　者：王煜坤 邵龙涛 余涛 耿泰[5] 徐征 周煜 WANG Yukun;SHAO Longtao;YU Tao;GENG Tai;XU Zheng;ZHOU Yu(Jincheng College,Nanjing University of Aeronautics and Astronautics,Nanjing 211156,China;College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Wuhan Second Ship Design and Research Institute,Wuhan 430205,China;Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;Zhongfa Aviation Institute,Beihang University,Hangzhou 311115,China)

机构地区：[1]南京航空航天大学金城学院,南京211156 [2]南京航空航天大学民航学院,南京211106 [3]北京航空航天大学能源与动力工程学院,北京100191 [4]武汉第二船舶设计研究所,武汉430205 [5]北京航空航天大学航空发动机研究院,北京100191 [6]北京航空航天大学中法航空学院,杭州311115

出　　处：《航空动力学报》2024年第12期9-19,共11页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2018YFB010400);国家自然科学基金(U2233213,52206131,51775025);浙江省自然科学基金(LQ22E060004);国家重点研发计划项目(2022YFB2602002)。

摘　　要：面向高功率密度和低耗油率,提出了一种航空活塞-涡轮复合循环动力系统构型,活塞子系统采用气缸水平对置的二冲程航空重油活塞发动机,涡轮机子系统由燃烧器和涡轮增压器组成。基于GTPOWER平台,采用缸压对比研究的方法验证了仿真模型的准确性。基于仿真模型研究了增压器效率、涡轮等熵效率、补燃油量及海拔高度对复合循环动力系统性能的影响,并依据油耗与输出扭矩进行系统性能评估。研究结果表明:与单一航空活塞发动机相比,混合动力系统在极限状态下能将输出扭矩提升约30%;压气机等熵效率提升10%产生的扭矩增益大于涡轮等熵效率提升10%产生的扭矩增益;涡轮前补燃燃油流量在0.2 g/s时,能够将排温提升约150 K,所有工况点输出扭矩提升20%以上。因此,涡轮前补燃是提升航空活塞-涡轮混合动力系统性能的有效手段。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.

关 键 词：二冲程航空活塞 混合动力系统 GT-POWER模拟 涡轮子系统效率 补燃 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]