Statistics and analysis of critical failures of F100 / F110 engine and F-15 / F-16 fighter during operation

LIANG Chun-hua; WANG Zhan-xue; CAO Mao-guo

Chinese

您当前的位置：

首页 >

文章列表页 >

Statistics and analysis of critical failures of F100 / F110 engine and F-15 / F-16 fighter during operation

更新时间：2026-07-07

- Statistics and analysis of critical failures of F100 / F110 engine and F-15 / F-16 fighter during operation
- Vol. 26, Issue 7, (2011)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,71007
  2. 中国航空工业集团公司沈阳发动机设计研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
移动端阅览
LIANG Chun-hua, WANG Zhan-xue, CAO Mao-guo. Statistics and analysis of critical failures of F100 / F110 engine and F-15 / F-16 fighter during operation[J]. 2011, 26(7).
DOI：

LIANG Chun-hua, WANG Zhan-xue, CAO Mao-guo. Statistics and analysis of critical failures of F100 / F110 engine and F-15 / F-16 fighter during operation[J]. 2011, 26(7). DOI：

摘要

为借鉴国外航空发动机在设计、研制和使用中积累的经验与教训

通过大量的数据统计与分析

描述美国F-15与F-16战斗机及其装配的F100与F110发动机在使用中发生的重大故障

归纳并总结这些故障在不同阶段、不同部件、不同影响因素的分布情况与规律.分析表明:发动机在前10年或工作35000h左右

故障率高

在之后的较成熟期

故障明显减少;无论是否考虑结构完整性

发动机各种故障会出现在整个使用过程中

但按结构完整性大纲研制的发动机的故障率明显低;在部件故障分布方面

发动机叶轮机是最主要的故障源;在影响因子分布方面

设计、维护、保障和使用不当是发动机出现故障的最主要原因.

Abstract

With reference to foreign experience on fighter engine design and development

the critical failures of F-15 and F-16 fighter powered by F100/F110 engine during operation were described based on a great deal of data statistics and analysis. The distribution and respective rules of the failures during operation phases

various components and influential factors were analyzed and concluded. The analysis shows that the failure rate of the engine is high within initial 10 years or 35000 flight hours

then significantly decreases; various engine failures can be exposed during operation

but the failure rate considering the structure integrity is obviously lower than that without considering the structure integrity; the compressor and turbine are main sources of failures; the design

maintenance

support and operation are main influential factors.

关键词

Keywords

references

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Inverse method for estimating the vibration stress of turbine blades based on combined high-and-low cycle fatigue tests

组合式弹性金属密封泄漏特性实验研究与结构优化

基于三维接触摩擦单元的套齿连接解析建模研究

与发动机匹配的旁路式双喉道气动矢量喷管数值模拟研究

基于自适应MOMEDA滚动轴承故障特征提取方法

Related Author

SUN Rui-jie

YAN Xiao-jun

NIE Jing-xu

Related Institution

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰