活塞式航空发动机二级涡轮增压系统匹配分析

Match analysis on two-stage turbo charging system of piston aero-engine

针对高空小型飞机的动力要求,对某一级增压的活塞式航空发动机进行了二级增压系统的匹配设计分析.利用AVL boost软件建立了原发动机的一级增压模型,并根据实验数据进行了校核.在原机模型的基础上,建立了二级增压发动机模型,并且进行了匹配计算.计算结果给出了发动机不同海拔高度下的运行情况,分析了发动机主要参数对性能的影响.研究了旁通阀对二级增压系统的调节规律,确定了高低两级压气机总压比随发动机海拔高度的变化趋势.结果表明,二级增压系统能够为发动机提供足够的进气充量,保证在大气密度降低后发动机还可以产生要求的功率,取得了预期的效果.

To reach the motive force requirement of high altitude light aero-plane, a two-stage turbo charging system matching design analysis was performed for a turbo charging piston aero-engine. The software package of AVL boost was used to establish a theoretical analytic model of the supercharged prototype engine. The model was verified and validated though experiments. The model of two-stage turbocharging engine was set up on the basis of the model of prototype engine, and the matching calculates had been done. The characteristics of engine in different altitude above sea level were calculated, and the effects of engine major parameters for the performance were analyzed. The rule of the bypass valve regulating the two-stage turbocharging system was studied. The variation trend of high and low stage compressor＇s total pressure ratio versus the different altitude was defined. The result shows that the two-stage turbocharging system can provide high boost pressure, which can be maintained the requested engine power. These work reaches the anticipated design object.