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.
作者
王波
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)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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)。
关键词
压气机稳定性
喘振
喘振检测
控制逻辑
消喘
逼喘
compressor stability
surge
surge detection
control logic
anti-surge
forced-surge
