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《中国安全生产科学技术》[ISSN:1673-193X/CN:11-5335/TB]

卷:

22

期数:

2026年5期

页码:

149-157

栏目:

火灾与爆炸安全

出版日期:

2026-05-30

文章信息/Info

Title:

Numerical simulation of fire in aircraft engine nacelle throughout the complete flight cycle

文章编号:

1673-193X(2026)-05-0149-09

作者:

周梓晨; 智茂永; 张明格; 赵海汇

(1.中国民用航空飞行学院 民航安全工程学院，四川 德阳 618307；
2.民机火灾科学与安全工程四川省重点实验室，四川 德阳 618307）

Author(s):

Zhou Zichen;  Zhi Maoyong;  Zhang Mingge;  Zhao Haihui

(1.Civil Aviation Flight University of China,College of Civil Aviation Safety Engineering,Deyang Sichuan 618307,China;
2.Civil Aircraft Fire Science and Safety Engineering Key Laboratory of Sichuan Province,Deyang Sichuan 618307,China)

关键词:

民用飞机; 发动机短舱; 油池火; PyroSim; 火灾模拟

Keywords:

civil aircraft;  engine nacelle;  pool fire;  PyroSim;  fire simulation

分类号:

X949；V328

DOI:

10.11731/j.issn.1673-193x.2026.05.018

文献标志码:

A

摘要:

为探究民用飞机在飞行过程中发动机短舱火灾的蔓延过程，基于PyroSim平台构建某型涡扇发动机舱的数值模型。从飞机起飞、巡航到着陆的整个飞行过程中，选取海拔高度0~12 000 m范围内的5种典型飞行工况，模拟分析发动机舱火灾初期的烟气蔓延特征以及烟气温度场、CO体积分数场的变化规律。研究结果表明：随着飞行高度增加，低的气压、空气密度与温度环境能够降低燃烧速率，延缓轰燃发生时间，并降低火源温度及稳定燃烧阶段的温度峰值，有害烟气及CO气体的蔓延速度加快，当飞行的海拔高度由2 000 m增加至7 000 m时，舱内最高温度由1 200 ℃降低至1 000 ℃，轰燃时间由20 s延迟至32 s，在起火10 s时CO体积分数峰值由0.07%增加至0.11%；在海拔高度为12 000 m的高空飞行条件下，泄漏的燃油难以维持燃烧，火灾发生可能性显著降低。研究结果可为发动机舱内的火灾探测器布局和报警阈值设定、防火材料选型以及不同飞行阶段的灭火剂喷射策略制定提供参考。

Abstract:

In order to investigate the development characteristics of engine nacelle fires in civil aircraft during flight,a detailed numerical model of a turbofan engine nacelle was established based on the PyroSim platform.During the whole flight process from take-off,cruise to landing,five typical flight conditions ranging from 0 to 0~12 000 m above sea level were selected to simulate and analyze the characteristics of smoke spread in the early stage of engine nacelle fire,as well as the changing laws of smoke temperature field and CO concentration field.The results indicate that the increase of flying height along with low air pressure,air density and temperature environment could suppress the combustion rate,delay the onset of flashover,and reduce both fire source temperature and peak temperature during stable combustion,and the spread of harmful flue gas and CO gas accelerated.When the altitude of flight increases from 2 000 m to 7 000 m,the maximum temperature in the cabin decreased from 1 200 ℃ to 1 000 ℃,the flashover time was delayed from 20 s to 32 s,and the peak value of CO concentration increased from 0.07 % to 0.11 % after 10 s of fire.Under the condition of flying at an altitude of 12 000 m,sustained combustion became difficult to maintain after fuel leakage,significantly lowering the probability of fire occurrence.The research results provide a basis for fire detectors layout in nacelle,the setting of alarm threshold,the selection of fire retardant materials and the formulation of fire extinguishing agent injection strategy in different flight stages.

备注/Memo

备注/Memo:

收稿日期： 2025-09-18；修回日期：2026-04-15
* 基金项目： 中国民用航空局民航安全能力建设项目（MHAQ2025023）；四川省科技计划项目（2025YFHZ0037）；中央高校基本科研业务费项目（24CAFUC01008）
作者简介： 周梓晨，硕士研究生，主要研究方向为航空消防救援。
通信作者： 智茂永，博士，教授，主要研究方向为航空安全和阻燃材料。

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更新日期/Last Update: 2026-06-03