某航空发动机喘振控制系统设计与验证  

Surge control system design and validation for an aero-engine

作　　者：王波[1,2] 张兴龙 张新非 车杰先 张天宏 WANG Bo;ZHANG Xinglong;ZHANG Xinfei;CHE Jiexian;ZHANG Tianhong(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Chengdu 610500,China;Project Management Center,Equipment Department of Air Force,People's Liberation Army,Beijing 100843,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空发动机集团有限公司四川燃气涡轮研究院,成都610500 [3]中国人民解放军空军装备部项目管理中心,北京100843

出　　处：《航空动力学报》2022年第5期1100-1112,共13页Journal of Aerospace Power

基　　金：国家航空专项基础研究(J2019⁃Ⅴ⁃0010)。

摘　　要：针对航空发动机易出现喘振误报、误判和消喘失败等问题,对某单轴带核心机驱动风扇(CDFS)的航空发动机对比分析不同的测点位置、信号处理、消喘控制逻辑设计下的消喘效果,并在高空模拟试验台上进行燃油阶跃逼喘验证。结果表明,测点2的A值脉动幅值是测点1的4倍,采用的硬件判喘准确率达到100%,制定的燃油阶跃供油控制方法可成功实现发动机逼喘,制定的消喘控制逻辑可成功使发动机退出喘振并恢复到目前状态。In view of the problems that aero-engines were prone to surge false alarm,misjudgment and failure of anti-surge,the anti-surge effects of a single-shaft aero-engine with core drive fan stage(CDFS)at different measurement points using different signal processing methods and anti-surge control logic designs were compared and analyzed. The surge control system was verified by the fuel step forced-surge on the high altitude simulation test. The results show that the pulsation amplitude of A value at the measurement point 2 is 4 times of that at the measurement point 1, and the accuracy of surge detection by hardware is 100%. The control method by fuel step can successfully realize the engine forced-surge,and the anti-surge control logic can successfully make the engine surge exit and restore to the present state.

关 键 词：压气机稳定性 喘振 喘振检测 控制逻辑 消喘 逼喘 

分 类 号：V233.95[航空宇航科学与技术—航空宇航推进理论与工程]