摘要
为了准确评估民用涡扇发动机空中起动试验性能与适航标准体系的符合性,在分析、解读中国民用航空局运输类飞机适航标准和美国联邦航空管理局咨询通告的基础上,制定了民用涡扇发动机空中起动飞行试验方案,以ARJ21-700型支线飞机配装的CF34-10A涡扇发动机合格审定试飞为平台,国内首次进行了相关试飞技术研究及飞行试验。试验结果表明:该空中起动飞行试验方案合理可行,能够完整、全面地验证民用涡扇发动机对适航标准体系的符合性。发动机最高起动边界为22500ft,起动高度指标设计合理,起动功能正常、可靠,满足适航标准要求。飞机待机状态双发失效后至起动成功高度损失为1457 ft,远小于适航标准规定的5000 ft指标。项目形成的试飞方案及积累的试飞经验为后续C919,C929等民用客机及其配装发动机的适航审定提供直接技术支持。
For verifying civil turbofan engine starting characteristics compliance with standards completely in flight test,the procedure of civil turbofan engine starting flight test was developed on the basis of analyzing and interpreting the chinese civil regulations transport airworthiness standards of Civil Aviation Administration of China & advisory circular of Federal Aviation Administration. It was applied in the ARJ21-700 aircraft flight test for the first time in China. The results show that the procedure of civil turbofan engine starting flight test is reasonable and feasible,and it is able to verify civil turbofan engine starting characteristics compliance with standards completely. The maximum starting altitude of CF34-10A engine was 22500ft,according with indications of design and airworthiness standards. The engine starting characteristics was trustworthy from the results of flight test. The aircraft flight altitude loss during double engine shutdown and starting period was 1457ft during the landing flight,which was less than 5000 ft of airworthiness standards. The procedure and experience of civil turbofan engine starting flight test directly provide support for flight test of C919,C929 civil aircrafts and equipped engines.
作者
赵海刚
屈霁云
符小刚
丁凯峰
杨东旭
ZHAO Hai-gang;QU Ji-yun;FU Xiao-gang;DING Kai-feng;YANG Dong-xu(Chinese Flight Test Establishment,Aviation Industry Corporation of China,Xi’an 710089,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2022年第4期347-354,共8页
Journal of Propulsion Technology
关键词
适航标准
涡扇发动机
飞行试验
起动特性
起动包线
Airworthiness standard
Turbo-fan engine
Flight test
Starting characteristics
Starting envelope
