第33卷第3期燃气涡轮试验与研究Vol.33,No.3 2020年6月Gas Turbine Experiment and Research Jun.,2020 严严
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收稿日期：2020-02-28
作者简介：陈博(1980-)，男，浙江湖州人，工程师，博士，主要从事飞机和发动机工程、飞行器控制等研究。 1引言
光纤调整架重点和难点问题，受到研究人员的广泛关注和重
视。据统计，美国在1982~1996年间发动机引起的
手机光线传感器
A类事故中高周疲劳故障占56%。1994年朝鲜半岛
局势紧张之时，美国空军主力战机F-15和F-16因
高周疲劳故障被限制使用和停飞，以至于美国在
1994年启动国家涡轮发动机高周疲劳科学与技术
计划(HCF计划)[1]，对发动机叶片高周疲劳问题进行 系统的深入研究[2]。我国的航空发动机自主研制起摘要：针对航空发动机涡轮整体叶盘叶片发生的高周疲劳裂纹故障，及排故初期受动应力测试条件限制，主要采取 增强结构抗力的排故措施使裂纹位置集中于叶片尾缘根部。后经高温、高转速、小尺寸整体叶盘叶片动应力测试技
术攻关，明确故障主要为涡轮导叶尾流激起的叶片振动应力超限所致。采取增加导叶数避开共振的改
进措施，并经
整机高周疲劳试验考核验证了其有效性。认识到叶片振动特性设计时需关注的几个问题，及先进动应力测试技术在
发动机研制过程中的不可或缺，形成了一套经过实践验证的叶片高周疲劳排故工作流程，对国内航空发动机研制起
到一定的参考借鉴作用。
关键词：航空发动机；涡轮叶片；高周疲劳；裂纹；振动应力测试；排故
中图分类号：V236文献标识码：A文章编号：1672-2620(2020)03-0033-04
Analysis and consideration for turbine blade high-cycle多功能开瓶器
fatigue crack failure of aero-engine
CHEN Bo1，ZHU Jian-han2，LU Hui-jun2
(1.Equipment Department of PLA Air Force，Beijing100843，China；
2.AECC Sichuan Gas Turbine Establishment，Chengdu610500，China)
Abstract：For high-cycle fatigue crack occurred in turbine disc blade of a certain aero-engine,due to the limitation of dynamic stress testing conditions at the initial stage,the cracks were concentrated at the root of the trailing edge of the blade by strengthening the structural resistance.Later,after a technical break⁃through in the dynamic stress test of high temperature,high speed and small size blisk blade,it was clear that the main reason for the failure was the over-limit vibration stress caused by the wake flow of turbine guide blade.Finally,the problem was solved by increasing the number of blades to avoid resonance,and the effectiveness of the method was verified by high-cycle fatigue test in the engine environment.Through the troubleshooting,it is understood that some issues should be paid attention to in the design of blade vibration characteristics.The dynamic stress test technology is indispensable in the aero-engine development,and a set of verified troubleshooting work flow is established,which can be referential for the domestic areo-en⁃gine development.
Key words：aero-engine；turbine blade；high-cycle fatigue；crack；dynamic stress test；troubleshooting
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