摘要
以研究航空发动机喷流起电的机理以及喷流起电对飞行器整体带电特性的影响为目的,对起电机理进行了建模和实验验证.首先以流体运动方程为基础,建立了航空发动机带电粒子浓度的动态仿真模型,仿真得到发动机燃烧过程中的各类粒子浓度变化情况.其次,设计了用于发动机喷流起电探测的静电感应传感器,对装配涡扇发动机的某型飞行器进行了地面试验测试,得到了发动机启动、稳定运行、加速、减速、停止等状态的动态电位.仿真及实验结果详细地描述了发动机喷流起电的机理,以及喷流起电会使飞行器带负电的结论,为进一步分析飞行器飞行过程中整体带电特性提供了指导.
To investigate the mechanism of electrification from aero-engine jet and the electrification effect on the overall charging charac-teristics of vehicle, a simulation model of concentration of charged particles in aero-engine is build based on the equations of fluid motion. And concentration changes of various particles are simulated. To verify the simulation result, a special electrostatic induction sensor for detecting the electrification of engine jet is designed, according to the principle of the Faraday cup, to measure the dynamic potential when the turbofan engine starts, operates steadily, accelerates, decelerates and stops. The simulation and experimental re-sults show that the aircraft is negatively charged by the electrification from aero-engine jet and the mechanism of electrification from aero-engine jet is described specifically. The research may provide a guidance to the further study on analyzing the overall charging characteristics of vehicle during the flight.
出处
《物理学报》
SCIE
EI
CAS
CSCD
北大核心
2013年第22期296-302,共7页
Acta Physica Sinica
基金
国家自然科学基金(批准号:61172035)资助的课题~~
关键词
航空发动机
喷流起电
传感器
aircraft engines, jet electrification, sensors
