运输类飞机涡轮发动机机匣烧穿适航符合性验证研究

Compliance Verification of Transport Aircraft Turbo-engine Case Burn-through

尽管涡轮发动机的设计水平在持续提升,但是服役经历表明涡轮发动机机匣烧穿事件仍在继续发生。本文分析了涡轮发动机机匣烧穿适航条款,总结了CCAR25.903(d)(1)中燃烧室机匣烧穿的适航符合性验证思路,并以某型飞机为例,建立机匣烧穿模型,确定受影响的关键部件和结构,并设计了火警探测系统及防护罩。验证表明,该型飞机满足适航条款要求。文章为运输类飞机进行相应设计考虑和符合性验证提供参考。

Although the design of turbine engines has continually improved over the years, service experience has shown that turbine engine case burn-through events continue to occur. The paper analyzed the airworthiness terms of turbo-engine case burn-through, summarized the compliance methodology of combustion chamber case burn-through in the CCAR25.903（d）（1）. Took one aircraft as an example, set up case burn through model, determined the affected key component and structure, designed the fire detection system and protector. The verification showed that, the aircraft satisifed the requirement of airworthiness terms. The paper provides a reference for the design precautions and compliance considerations of civil transport aircraft.