涡扇发动机消喘系统飞行试验验证方法研究  

Study on flight test verification method of turbofan engine surge elimination system

作　　者：申世才[1] 周超 高磊[1] SHEN Shi-cai;ZHOU Chao;GAO Lei(Engine Flight Test Technology Institute of Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院发动机所,西安710089

出　　处：《燃气涡轮试验与研究》2019年第1期43-46,共4页Gas Turbine Experiment and Research

摘　　要：针对涡扇发动机消喘系统飞行试验验证需求,和传统试验方法不能有效验证消喘结束后发动机状态恢复能力的问题,根据消喘系统工作原理,提出了单次喘振和连续多次喘振下消喘系统的飞行试验验证方法。该方法通过加装座舱开关,触发发动机调节器内设置的喘振模拟模块,发出根据真实喘振信号特征设计的喘振模拟信号,从而使得消喘系统工作,验证飞行状态下发动机消喘系统对短时切油、喷口面积和可调导叶的控制及消喘结束后发动机状态恢复的能力。试验结果表明:所提出的方法能有效验证消喘系统的功能及消喘结束后发动机状态恢复的能力。本研究对发动机消喘系统可靠性和有效性的飞行试验鉴定具有一定的工程应用价值。In order to meet the flight validation requirements of turbofan engine surge elimination system and to effectively validate the engine recovery ability after surge elimination, a flight test validation method of surge elimination system with single surge and continuous multiple surge was proposed according to the working principle of surge elimination system. In this method, the cockpit switch was installed to trigger the surge simulation module set in the engine regulator to send out a surge simulation signal based on the char. acteristics of a real surge signal, so as to make the surge elimination system work. The surge elimination sys. tem control of fuel cutting for a short time, nozzle area and adjustable guide vane in flight and the engine re. covery ability after surge elimination was validated. The results indicate that this method can effectively ver. ify the function of surge elimination system and engine recovery ability after surge elimination. This study provides important engineering application reference for reliability of surge elimination system and validity of flight testing.

关 键 词：航空发动机 消喘系统 连续喘振 恢复能力 座舱开关 喘振模拟 飞行试验 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]