风扇/压气机叶片外物损伤验证方法及疲劳强度预测研究  

Verification Method of Foreign Object Damage and Fatigue Strength Prediction of Fan/Compressor Blades

作　　者：张涛 赵振华[2] 杜文军 周留成[3] 王凌峰 ZHANG Tao;ZHAO Zhen-hua;DU Wen-jun;ZHOU Liu-cheng;WANG Ling-feng(AEEC Sichuan Gas Turbine Establishment,Chengdu 610500,China;State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Science and Technology on Plasma Dynamics Laboratory,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川成都610500 [2]南京航空航天大学机械结构力学及控制国家重点实验室,江苏南京210016 [3]空军工程大学等离子体动力学重点实验室,陕西西安710038

出　　处：《推进技术》2023年第2期239-244,共6页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅳ-0014-0082)。

摘　　要：为了在部件试验器上验证发动机风扇/压气机叶片的抗外物损伤的能力,针对某型航空发动机高压压气机叶片,开展了叶片的外物损伤试验和损伤叶片的高周疲劳试验,提出了叶片预制缺口位置、深度的确定方法以及根据动应力测试数据确定振动疲劳试验载荷的方法。使用最差缺口模型对损伤叶片进行了疲劳强度的预测与评估,结果表明,该模型对带缺口试样疲劳强度的预测偏危险,在工程使用时建议取1.5倍安全系数。In order to verify the resistance of the anti foreign object damage(FOD) design of fan/compressor blades on bench test, FOD tests and high cycle fatigue tests were carried out for damaged high-pressure compressor blades of certain aero-engine. The position and depth determination method of preformed notch blade and the vibration fatigue test load determination method according to the dynamic stress test data are proposed. The worst case notch model was used to predict and evaluate the fatigue strength of damaged blades, results show that the model tends to be dangerous in predicting the fatigue strength of notched samples, and it is recommended to take 1.5 times the safety factor in engineering application.

关 键 词：风扇/压气机叶片 外物损伤 疲劳强度 验证方法 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]