某型航空发动机涡轮叶片服役微观损伤研究

doi:10.3901/JME.2019.13.122

机械工程学报 ›› 2019, Vol. 55 ›› Issue (13): 122-128.doi: 10.3901/JME.2019.13.122

• 特邀专栏：航空发动机健康监测与故障诊断 • 上一篇下一篇

某型航空发动机涡轮叶片服役微观损伤研究

范永升¹, 黄渭清¹, 杨晓光^1,2, 石多奇^1,2

1. 北京航空航天大学能源与动力工程学院北京 100191;
2. 北京航空航天大学航空发动机结构强度北京市重点实验室北京 100191

收稿日期:2018-07-20 修回日期:2019-02-07 出版日期:2019-07-05 发布日期:2019-07-05
通讯作者: 杨晓光(通信作者),男,1962年出生,博士,教授,博士研究生导师。主要研究方向为金属本构理论与材料高温疲劳与断裂,航空发动机结构完整性。E-mail:yxg@buaa.edu.cn
作者简介:范永升,男,1993年出生,博士研究生。主要研究方向为航空发动机高温结构强度。E-mail:fanys@buaa.edu.cn
基金资助:
国家重点基础研究发展计划资助项目（973计划，2015CB057401）。

Microstructural Damage Analysis of Service Turbine Blades for an Aero-engine

FAN Yongsheng¹, HUANG Weiqing¹, YANG Xiaoguang^1,2, SHI Duoqi^1,2

1. School of Energy and Power Engineering, Beihang University, Beijing 100191;
2. Beijing Key Laboratory of Aero-engine Structure and Strength, Beihang University, Beijing 100191

Received:2018-07-20 Revised:2019-02-07 Online:2019-07-05 Published:2019-07-05

摘要/Abstract

摘要： 涡轮叶片是航空发动机工作条件最为恶劣的热端部件，其工作性能的优劣决定着整机能否高效、安全、可靠工作。涡轮叶片在服役过程中不可避免地形成各类损伤，由于涡轮叶片制造复杂、造价昂贵，因此对涡轮叶片的服役损伤进行分析和梳理，使涡轮叶片得到安全可靠且充分有效的使用，具有重要的经济价值。利用金相观察、SEM分析和EDS分析等方法对某型航空发动机第一级高压涡轮叶片在服役过程中产生的微观损伤进行分析。结果表明该型航空发动机涡轮叶片的微观损伤以强化相的粗化和筏化为主。以此为基础建立了一套以强化相尺寸为指标的涡轮叶片服役微观损伤表征方法。对服役涡轮叶片开展了硬度测试试验，结果发现随着微观组织的退化，叶片各个部位的维氏硬度出现不同程度的下降。随后，对热暴露预损伤涡轮叶片材料薄壁试样在850℃/810 MPa考核条件下开展了低周疲劳试验。结果表明随着微观组织的退化，合金的低周疲劳性能出现了不同程度的下降，说明服役微观损伤降低了涡轮叶片材料的抗疲劳性能。

关键词: 低周疲劳, 服役, 微观损伤, 涡轮叶片, 硬度

Abstract: Working under the severest condition, turbine blade is the most important and crucial part of aero-engine. The working performance of the whole aero-engine highly depends on turbine blades. Damage inevitably occurs on the turbine blades during operation. As turbine blades are expensive and difficult to manufacture, ensuring the blades work reliably and making full of the turbine blades are important for safety service aero-engine. The microstructural damage in the service process of the turbine blade of an aero engine is investigated and summarized. The results show that the microstructural damage is mainly based on the coarsening and rafting of the precipitate phases. A set of evaluation methods characterized by precipitate phase size is established. Hardness test of turbine blades is carried out. The result shows that with the degradation of microstructure, the hardness in various positions of the blades decreased. Finally, the low cycle fatigue test was carried out at 850℃/810 MPa for different heat exposure conditions of the turbine blade materials. The results show that with the degradation of microstructure, the low cycle fatigue properties of the alloy decreased, indicating that the fatigue resistance of the turbine blade materials declined with microstructural damage.

Key words: hardness, low cycle fatigue, microstructural damage, service, turbine blades

中图分类号:

V223

范永升, 黄渭清, 杨晓光, 石多奇. 某型航空发动机涡轮叶片服役微观损伤研究[J]. 机械工程学报, 2019, 55(13): 122-128.

FAN Yongsheng, HUANG Weiqing, YANG Xiaoguang, SHI Duoqi. Microstructural Damage Analysis of Service Turbine Blades for an Aero-engine[J]. Journal of Mechanical Engineering, 2019, 55(13): 122-128.

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某型航空发动机涡轮叶片服役微观损伤研究

Microstructural Damage Analysis of Service Turbine Blades for an Aero-engine

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