摘要
介绍了涡轮榫接结构疲劳寿命评估技术的研究现状,分别从多场载荷分析、裂纹萌生寿命评估、裂纹扩展模拟和试验技术等方面探讨了现有研究的进展、不足以及发展趋势,重点论述了涡轮榫接结构使用寿命和损伤容限的评估方法。结果表明:现有的分析和试验方法能基本实现涡轮榫接的疲劳寿命评估,但由于各种局限性,工程适用性亟待提高,仍需稳健的载荷降阶分析方法、基于物理机制和数据驱动的寿命评估方法、载荷历程相关的裂纹扩展寿命评估方法和复杂热力环境下的试验技术,从而建立先进航空发动机涡轮榫接结构疲劳寿命评估及验证体系。
Research related to fatigue life assessment of turbine attachment was introduced.The progress,shortcomings,and development trends of existing research were discussed in terms of multi-field load analysis,crack initiation life assessment,crack propagation analysis,and test techniques,respectively,focusing on the methods for assessing the service life and damage tolerance of turbine attachment.The results show that the existing analysis and test methods can basically achieve the fatigue life assessment of turbine attachment,but due to various limitations,the engineering applicability needs to be improved.It is necessary to conduct research on robust reduction order methods for load analysis,life assessment methods based on physical mechanisms and data-driven,crack growth simulation under variant loading amplitude,and test techniques in complex thermomechanical environments,and to develop a system to support the fatigue life assessment and validation of turbine attachment in advanced aero-engine.
作者
胡殿印
鄢林
李鑫
张晓杰
毛建兴
古远兴
王荣桥
HU Dianyin;YAN Lin;LI Xin;ZHANG Xiaojie;MAO Jianxing;GU Yuanxing;WANG Rongqiao(Research Institute of Aero‑Engine,Beihang University,Beijing 100191,China;Beijing Key Laboratory of Aero‑Engine Structure and Strength,Beihang University,Beijing 100191,China;United Research Center of Mid‑Small Aero‑Engine,Beijing 100191,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou 412002,China;Sichuan Gas Turbine Research Institute,Aero Engine Corporation of China,Chengdu 621300,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2023年第4期573-588,共16页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(52022007)
国家科技重大专项(2017-IV-0004-0041,J2019-IV-0009-0077,J2019-IV-0016-0084)
关键词
涡轮榫接
多场载荷
复合疲劳
裂纹萌生
裂纹扩展
试验验证
turbine attachment
multi-physical field loads
combined fatigue
lifetime assessment
crack growth
experimental verification
作者简介
胡殿印,女,教授,博士生导师,国家级领军人才,研究方向为发动机结构强度及疲劳可靠性。主持“两机”基础研究项目、工信部民机科研、科工局技术基础项目、国家自然科学基金、教育部博士点基金、航空科学基金、产学研基金等30余项,授权国家发明专利50余项,发表SCI、EI论文130余篇,主编出版学术专著2部、教材1部,获省部级科技奖励3项;通信作者:胡殿印,E-mail:hdy@buaa.edu.cn。
