二冲程航空活塞发动机增压匹配研究和优化  

Research and Optimization of Turbocharging Matching for Two-stroke Aero Engine

作　　者：张朔 赵振峰[1] 董雪飞 叶莹[1] ZHANG Shuo;ZHAO Zhenfeng;DONG Xuefei;YE Ying(School of Mechanical Engineering,Beijing Institute of Technology,Beijing 100081,China;Beijing Aerospace UAV System Engineering Research Institute,Beijing 100094,China)

机构地区：[1]北京理工大学机械与车辆学院,北京100081 [2]北京航天无人机系统工程研究所,北京100094

出　　处：《兵工学报》2020年第1期135-142,共8页Acta Armamentarii

基　　金：装备预先研究项目(201720301146)

摘　　要：针对二冲程航空活塞发动机高空功率下降问题开展增压匹配的相关研究。建立二冲程非增压航空活塞发动机的一维仿真模型,并对仿真模型进行了实验验证;以校验后的非增压发动机模型为基础匹配了增压器,建立增压发动机模型。通过废气涡轮增压匹配进行不同海拔高度条件下的匹配计算;研究高空环境下二冲程增压发动机的工作情况,提出利用排气系统结构优化拓宽增压器的工作范围,利用废气旁通阀控制增压程度方法对增压系统进行优化。获得了在7000 m海拔高度能够实现76%功率恢复的增压型二冲程航空活塞发动机,满足某无人机平台飞行任务剖面对发动机的需求。The turbocharging matching is researched for the problem of power reduction of two-stroke aero engines at high-altitudes.An one-dimensional simulation model of a natural aspirated two-stroke aero engine was established and experimentally verified.Based on the verified model,a turbocharger is matched,and a turbocharged engine model is established.The structure optimizing and control strategies of bypass valve in exhaust system are proposed to broaden the working range of turbocharger through the calculation and analysis of turbocharging matching at variable altitudes.A two-stroke turbocharged aero engine with 76%power recovery at 7000 m altitude was designed,which can meet the demand of an unmanned aerial vehicle’s mission profile.

关 键 词：航空活塞发动机 二冲程 增压匹配 无人机 涡轮增压 高空功率恢复 

分 类 号：V234[航空宇航科学与技术—航空宇航推进理论与工程] V249