航空二冲程活塞发动机分层扫气优化  

Stratified Scavenging Optimization of Aircraft Two-stroke Piston Engine

作　　者：黄云龙 杨广文 李洲 HUANG Yun-long;YANG Guang-wen;LI Zhou(Nanjing Research Institute on Simulation Technique,Nanjing 210016,China)

机构地区：[1]南京模拟技术研究所,南京210016

出　　处：《航空发动机》2023年第1期47-52,共6页Aeroengine

基　　金：国家重点研发计划项目(2017YFD0701003)资助。

摘　　要：针对二冲程活塞发动机常规扫气短路损失大、油耗高的问题,提出了一种分层扫气方案并进行了优化。以某发动机为研究对象,采用数值模拟方法建立了分层扫气模型,并对分层扫气过程进行了3维CFD仿真,其计算所需的边界条件通过发动机整体性能1维仿真获得,采用该模型研究了分层扫气发动机扫气机理,对不同容积扫气道进行了仿真,并对二冲程扫气过程的过量充气系数、扫气效率等参数进行对比。在仿真优化研究的基础上加工优化后的扫气道盖实物,并结合发动机巡飞工况状态开展发动机性能对比试验。结果表明:采用分层扫气过程的短路损失相比于常规扫气过程的减小42%,扫气道容积提高到1.3倍可使扫气效率提高2%,相比原型机测试数据,配置1.3倍扫气道容积的发动机在巡航转速范围内,燃油消耗率降低10%,但发动机功率略有降低。Aiming at the problem of huge scavenging short-circuiting loss and high fuel consumption of two-stroke piston engine,a stratified scavenging plan was proposed and optimized.A stratified scavenging model for an engine was established,and the stratified scavenging process was simulated by three-dimensional CFD.The boundary conditions required for the three-dimensional calculation were obtained from the one-dimensional simulation of the overall engine performance.Based on the model,the scavenging mechanism of the engine using stratified scavenging was studied,simulations of different transfer passage volumes were conducted,and the parameters such as overcharging coefficient and scavenging efficiency were compared in two-stroke scavenging processes.On the basis of simulation and optimization,the optimized scavenging port cover was fabricated,and the engine performance comparison tests were carried out under engine cruising conditions.The results show that the stratified scavenging short-circuiting loss is reduced by 42%compared with the conventional scavenging process,and the scavenging efficiency is increased by 2%when the transfer passage volume is 1.3 times the original volume.Compared with the prototype test data,the fuel consumption rate of the engine equipped with 1.3 times the volume of the scavenging port is reduced by 10%within the cruise speed range,but the engine power is slightly reduced.

关 键 词：航空二冲程活塞发动机 分层扫气 数值模拟 短路损失 扫气效率 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]