小型涡扇发动机全状态实时数值仿真  

All State Real-time Numerical Simulation of a Small-sized Turbofan Engine

作　　者：王汉权[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2014年第2期61-67,共7页Tactical Missile Technology

摘　　要：介绍了小型涡扇发动机全状态实时数值仿真的建模方法。发动机采用基于特性的部件级模型,考虑了燃烧室、内涵喷管、外涵通道、高-低压涡轮过渡通道和风扇-压气机过渡通道的容积效应。燃油控制装置模型按照传感器、控制器、调节器等模块原理建立,考虑了大于0.01 s时间常数的惯性环节影响。该仿真程序为全状态、大偏离、动/稳态、具备实时能力的数值仿真模型,通过时间步长的数值积分完成,无需迭代、速度快,能够满足工程要求。本模型以动力装置各主要部件的试验特性为基础进行解算,保证了仿真结果的精确性。An all state real-time numerical simulation of small-sized turbofan engine is introduced. The engine model adopts the component level model based on characteristics, considering volume dynamics of the combustion chamber, the connotation nozzle, the outside duct, the high-low pressure turbine transi- tion channel and the fan-compressor transition channel. The fuel control unit model is established ac- cording to some principles of the sensor, the controller and the regulator and so on. The model has mainly considered about effect of the inertia ring which is more than 0.01 second. This simulation pro- gram is a simulation model of the whole state, the full envelope, great deviation, dynamic/static and real-time ability, by means of time the step numerical integration completees, no iterative and velocity quickly, the performance can meet the engineering requirements. The experiment performance with a series of main components of the engine is used to solve the model, it can guarantee exact quality of simulation result.

关 键 词：实时模型 容积动力学 无迭代法 燃气涡轮发动机 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]