高空试车台供气压缩机组动态仿真建模方法研究  

Dynamic Simulation Method for Air Supply Compressor Unit of Altitude Test Facility

作　　者：苏阳 王信 陈雪江[1] 艾文森 王同庆 李晓冬 刘晓明 SU Yang;WANG Xin;CHEN Xue-jiang;AI Wen-sen;WANG Tong-qing;LI Xiao-dong;LIU Xiao-ming(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;AECC Sichuan Gas Turbine Establishment,Mianyang 621703,China;State Key Laboratory of Compressor Technology,Hefei General Machinery Research Institute Co.,Ltd.,Hefei 230031,China)

机构地区：[1]西安交通大学能源与动力工程学院,陕西西安710049 [2]中国航发四川涡轮研究院,四川绵阳621703 [3]合肥通用机械研究院有限公司压缩机技术国家重点实验室,安徽合肥230031

出　　处：《推进技术》2022年第10期370-377,共8页Journal of Propulsion Technology

基　　金：中国航发四川燃气轮机研究院稳定支持项目(GJCZ-0013-19);压缩机技术国家重点实验室开放基金(SKLYSJ202007)。

摘　　要：针对国内高空试车台研究中缺少对供气压缩机组动态仿真研究方法的现状,提出了一种适用于该热力系统的动态仿真建模方法。基于守恒方程,获得了压缩机、管网、换热器、调节阀的动态仿真计算模型;将Greitzer压缩机模型应用到复杂热力系统的动态建模中;在容腔模型的基础上增加流动损失计算模块,提出了“容腔-损失”管网模型。在Matlab/Simulink平台上搭建了试车台供气压缩机组动态仿真模型。将仿真结果与实验结果对比,验证压缩机、管网等部件动态仿真模型的可靠性。其中,压力、温度的仿真结果的平均误差均小于1%;与传统的容腔模型相比,“容腔-损失”管网模型误差明显减小。证明了该建模方法的精确度与可靠性。In view of the lack of simulation methods for air supply compressor unit of altitude test facility(ATF)interiorly,a universal thermal dynamic simulation method is proposed. Based on conservation equations,the dynamic simulation models for compressor,ducting,valve and heat exchanger are obtained. Greitzer model for compressor is applied to the dynamic modelling of complex thermodynamic systems. Based on the cavity model,the flow loss calculation module is added to optimize the flow loss calculation module,and the pipeline model considering the loss is proposed. Finally,the dynamic simulation model of a gas supply compressor unit of ATF is built on the Matlab/Simulink platform. The reliability of the dynamic simulation model for each component is verified by comparing with the experimental results. The average error of simulation results of pressure and temperature is less than 1%. Compared with the traditional cavity model,the error of the pipeline model considering the loss is significantly reduced. The accuracy and reliability of the modeling method are proved.

关 键 词：航空发动机 试车台 压缩机组 管网建模 动态仿真 热力系统 

分 类 号：V231.11[航空宇航科学与技术—航空宇航推进理论与工程]