某型发动机进气机匣高循环疲劳失效分析及解决方法
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- 英文论文题名：High Cycle Fatigue(HCF) Failure Analysis and Solution of Gas Turbine Inlet Casing
- 论文作者：刘洋
- 英文论文作者：LIU Yang ; AVIC Shenyang Aero Engine Design and Research Institute
- 年：2016
- 作者机构：中航工业沈阳发动机设计研究所;
- 论文关键词：高循环疲劳 ; 失效分析 ; 振动应力 ; 航空发动机
- 英文论文关键词：high cycle fatigue(HCF) ; failure analysis ; vibration stress ; aero engine
- 会议召开时间：2016-07-15
- 会议录名称：2016航空试验测试技术学术交流会论文集
- 语种：中文
- 分类号：V231.95
- 学会代码：ZGHU
- 学会名称：中国航空学会
- 页数：3
- 文件大小：475k
- 原文格式：O
摘要
针对航空发动机工作中出现的进气机匣高循环疲劳失效问题进行分析解决。由故障位置断口分析结果确定其故障为典型的结构件高循环疲劳(HCF)失效,通过模态试验和坎贝尔图分析获得发动机工作转速范围内需重点关注的共振频率及振型,进行动应力测试确定故障位置振动响应与模态结果相符,再用古德曼图分析,发现测得应力值满足设计强度储备,判断该断口故障并非单一的高循环疲劳失效问题。检查机匣故障位置加工情况,确定断口故障系伴有应力集中的高循环疲劳失效问题,提出两种排故方法,进行动应力测试验证排故措施有效。
Some methods such as model test,vibration stress test and fracture analysis are mentioned to solve HCF failure of inlet casing.The failure is recognized as HCF failure according to the results of fracture analysis.The possible resonance model under the operating condition of gas turbine is obtained based on Campbell diagram and the modal test results.The actually resonances including frequency and vibration stress are acquired through vibration stress test.Based on the results above and using Goodman diagram analysis,it is found that the vibrating strength safety factor is higher than the design requirement.As a result,HCF failure happened on the inlet casing should not be considered as the failure affected by single factor.Some other factors should be considered during the trouble-shooting such as the machining process,the structure which should result in stress concentration etc is finally confirmed to be the factors that result in the failure of inlet casing besides resonance.Moreover,some improvements which finally validated through vibration stress test are advanced.
Some methods such as model test,vibration stress test and fracture analysis are mentioned to solve HCF failure of inlet casing.The failure is recognized as HCF failure according to the results of fracture analysis.The possible resonance model under the operating condition of gas turbine is obtained based on Campbell diagram and the modal test results.The actually resonances including frequency and vibration stress are acquired through vibration stress test.Based on the results above and using Goodman diagram analysis,it is found that the vibrating strength safety factor is higher than the design requirement.As a result,HCF failure happened on the inlet casing should not be considered as the failure affected by single factor.Some other factors should be considered during the trouble-shooting such as the machining process,the structure which should result in stress concentration etc is finally confirmed to be the factors that result in the failure of inlet casing besides resonance.Moreover,some improvements which finally validated through vibration stress test are advanced.
引文
[1]陈光,洪杰,马艳红.航空燃气涡轮发动机结构设计[M].北京航空航天大学出版社,2010.
[2]Federal Aviation Administration.FAR33 Federal Aviation Regulations Part 33[S].2009:28-30.
[2]Federal Aviation Administration.FAR33 Federal Aviation Regulations Part 33[S].2009:28-30.