Simulation and failure analysis of aircraft engine's bleed valve mechanism based on virtual prototyping technology

XIE Meng-tao; LU Shan; CHEN Yang-hui

doi:10.13224/j.cnki.jasp.2016.01.011

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Simulation and failure analysis of aircraft engine's bleed valve mechanism based on virtual prototyping technology

更新时间：2026-07-07

- Simulation and failure analysis of aircraft engine's bleed valve mechanism based on virtual prototyping technology
- Vol. 31, Issue 1, Pages: 78-83(2016)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,710072
  2. 中国航空工业集团公司西安航空发动机(集团)有限公司,西安,710021
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.01.011
  CLC：
- Published：2016
- 稿件说明：
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解梦涛, 陆山, 陈养惠. 基于虚拟样机技术的航空发动机放气活门机构仿真及故障分析[J]. 航空动力学报, 2016, 31(1): 78-83.

doi: 10.13224/j.cnki.jasp.2016.01.011
解梦涛, 陆山, 陈养惠. 基于虚拟样机技术的航空发动机放气活门机构仿真及故障分析[J]. 航空动力学报, 2016, 31(1): 78-83. DOI： 10.13224/j.cnki.jasp.2016.01.011.

doi: 10.13224/j.cnki.jasp.2016.01.011 DOI：

摘要

针对某型航空发动机放气活门机构主动摇臂的多起断裂故障

为寻找故障原因并尽可能缩短排故周期与降低排故成本.借助虚拟样机技术建立此机构的动力学仿真模型

利用动力学仿真软件ADAMS与有限元分析软件ANSYS的联合仿真分析

实现放气活门机构摇臂断裂故障再现

并找出断裂件受力的主要影响因素及其影响规律

估算各受力水平下断裂摇臂的疲劳寿命.最终

分别给出保证摇臂最低使用寿命与全寿命使用情况下的改进建议

即将摇臂与放气活门之间间隙B增大至0.273mm与0.279mm

从而为实际工程排故提供理论依据.

Abstract

For many rocker fractures of a certain type of aircraft engine's bleed valve mechanism

a dynamic model of the mechanism was built in order to obtain the fault reason and reduce the time and cost of the troubleshooting. The fault recurrence of the mechanism was implemented based on virtual prototyping technology by ADAMS and ANSYS software. The influence factor and law of fractured component's stress was found out

and the fatigue life of some stress levels was estimated. Finally

improvement proposals for increasing the gap B to 0.273mm and 0.279mm to ensure the rocker's shortest life and whole life were given respectively. Thus

the basis for the troubleshooting in engineering was provided.

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