Test method for the combined high and low cycle fatigues of turbine blade based on the whole engine operation
-
摘要: 针对航空发动机涡轮叶片同时承受高循环载荷和低循环载荷的特征,以小推力涡喷发动机为研究对象,搭建了基于引电器的涡轮叶片动应力测量系统,利用数值模拟和试验测试结合的方法,实现了高度为30mm的涡轮叶片在40000r/min转速、950℃环境温度条件下的动应力测量,并以此为基础发展了整机高低循环复合疲劳试验方法,开展了高压涡轮叶片高低复合疲劳整机试验。研究结果表明,该型发动机转速在34920r/min时,叶片高循环振动应力达到112.7MPa,带来了涡轮叶片的高循环疲劳损伤且是引起涡轮叶片产生裂纹的主要因素,低循环疲劳载荷是导致裂纹扩展的主要因素,两者综合作用会显著影响涡轮叶片寿命。Abstract: The turbine blade is subjected to both high cycle and low cycle loads synchronously during aero-engine operation. Therefore, using a low thrust turbojet engine as research platform, a test scheme based on the electrical leads on how to assess the blade dynamic stress was put forward in particular for the blades used in harsh conditions i.e. high rotation speed, small size and high temperature. The dynamic stress of 30mm height turbine blades operated at the rotation speed of 40000r/min and in 950℃ was obtained by use of a combined value simulation and experiment measurement method. Moreover test methods of the combined high cycle and low cycle fatigues based on the whole engine operation, including the methods on how to obtain the resonance vibratory stress and to compose the load spectrum, were developed. The engine test was carried out and the combined high cycle and low cycle fatigues of high pressure turbine blade were investigated. The results show that blade dynamical stress reaches 112.7MPa at the rotation speed of 34920r/min, which may lead to the high cycle fatigue failure of the turbine blade and the high cycle load is the major reason for the initialization of the crack, and the low cycle load is the major reason to result in the crack propagation, and both of them will affect the life of the turbine blade synthetically.
-
[1] ZHANG Dayi,HONG Jie,MA Yanhong,et al.A probability method for prediction on high cycle fatigue of blades arisen by aerodynamic loads[J].Advances in Engineering Software,2011,42(12):1059-1073. [2] DUGGAN T V,BYRENE J.Fatigue as a design criterion[M].London:Macmillan,1977. [3] HOU N X,WEN Z X,YU Q M,et al.Application of a combined high and low cycle fatigue life model on life prediction of SC blade[J].International Journal of Fatigue,2009,31(4):616-619. [4] PETERS J O,RITCHIE R O.Influence of foreign-object damage on crack initiation and early crack growth during high-cycle fatigue of Ti-6Al-4V[J].Engineering Fracture Mechanics,2002,67(3):193-207. [5] BYRNE J,HALL R F,POWELL B E.Influence of LCF overloads on combined HCF/LCF crack growth[J].International Journal of Fatigue,2003,25(9):827-834. [6] MATIKAS T E.A high-cycle fatigue apparatus at 20 kHz for low-cycle fatigue/high-cycle fatigue interaction testing[J].Fatigue & Fracture of Engineering Materials & Structures,2001,24(10):687-697. [7] 赵振华,陈伟.高低周循环复合载荷对TC11钛合金疲劳性能的影响[J].航空动力学报,2011,26(11):2468-2474.ZHAO Zhenhua,CHEN Wei.Effect of combined cycle load upon the fatigue performance of titanium alloy TC11[J].Journal of Aerospace Power,2011,26(11):2468-2474.(in Chinese) [8] 李睿,鲍蕊,费斌军.2024-T3铝合金孔板高低周循环复合疲劳试验研究[J].飞机设计,2010,30(3):18-22.LI Rui,BAO Rui,FEI Binjun.Experimental investigation on combined high and low cycle fatigue performance of 2024-T3 aluminum alloy plate with hole[J].Aircraft Design,2010,30(3):18-22.(in Chinese) [9] 刘红彬,陈伟,杜文军.TC11材料高低周循环复合疲劳试验研究[J].燃气涡轮试验与研究,2011,24(2):23-26.LIU Hongbin,CHEN Wei,DU Wenjun.Experimental investigation on low and high cycle combined fatigue performance of TC11 titanium alloy[J].Gas Turbine Experiment and Research,2011,24(2):23-26.(in Chinese) [10] 康宁,闫晓军,李晓甫,等.高低周循环复合疲劳试验中振动应力的监测与计算[J].燃气涡轮试验与研究,2010,23(4):22-25.KANG Ning,YAN Xiaojun,LI Xiaofu,et al.Numerical calculation and measurement of the vibration stress in combined high and low cycle fatigue tests[J].Gas Turbine Experiment and Research,2010,23(4):22-25.(in Chinese) [11] 闫晓军,孙瑞杰,邓瑛,等.涡轮叶片复合疲劳特性曲线及其规律的试验[J].航空动力学报,2011,26(8):1824-1829.YAN Xiaojun,SUN Ruijie,DENG Ying,et al.Experimental study on fatigue curve law of turbine blade under combied high and low cycle loading[J].Journal of Aerospace Power,2011,26(8):1824-1829.(in Chinese) [12] 侯贵仓,王荣桥,闫晓军,等.轮盘榫齿高低循环复合疲劳寿命试验研究[J].北京航空航天大学学报,1999,25(2):167-170.HOU Guicang,WANG Rongqiao,YAN Xiaojun,et al.Experiment study on combined fatigue of turbine disc fir-tree slots at elevated temperature[J].Journal of Beijing University of Aeronautics and Astronautics,1999,25(2):167-170.(in Chinese) [13] 洪杰,刘书国,张大义,等.小型短寿命涡扇发动机涡轮叶片疲劳失效分析[J].航空动力学报,2012,27(3):604-609.HONG Jie,LIU Guoshu,ZHANG Dayi,et al.Fatigue failure analysis of turbine blade in miniature short-life turbofan engine[J].Journal of Aerospace Power,2012,27(3):604-609.(in Chinese) [14] DEANNA R G.Wireless telemetry for gas-turbine engine[R].NASA/TM-2000-209815,2000. [15] LONG S A,EDNEY S L,REIGER P A,et al.Telemetry system integrated in a small gas turbine engine[J].Journal of Engineering for Gas Turbines & Power,2012,134(4):044501.1-044501.5. [16] 李仙丽,罗乘川,安奕忱,等.基于遥测技术的发动机涡轮转子叶片动应力测量[J].燃气涡轮试验与研究,2014,27(6):53-56.LI Xianli,LUO Chengchuan,AN Yichen,et al.Measuring technology on dynamic stress of turbine rotor blades using telemetry[J].Gas Turbine Experiment and Research,2014,27(6):53-56.(in Chinese) [17] 曹昆华,黄家经.某型发动机低压涡轮转子叶片动测技术及应用研究[J].燃气涡轮试验与研究,2008,21(1):22-25.CAO Kunhua,HUANG Jiajing,Investigation on the dynamic instrumentation technology of an engine LP turbine blade and its appliction[J].Gas Turbine Experiment and Research,2008,21(1):21-25.(in Chinese) [18] 卢艳辉,梅庆,雷沫枝,等.高转速压气机转子叶片的动应力测试与动力学设计评估[J].推进技术,2014,35(10):1398-1403.LU Yanhui,MEI Qing,LEI Mozhi,et al.Vibration stress test and dynamical evaluation for high rotational speed compressor blades through numerical and experimental method[J].Journals of Propulsion Technology,2014,35(10):1398-1403.(in Chinese) [19] 王桂华,刘海年,张大义,等.航空发动机成附件振动环境试验剖面确定方法研究[J].推进技术,2013,34(8):1101-1107.WANG Guihua,LIU Hainian,ZHANG Dayi,et al.Study on formulating method for vibration environment test profiles of aero-engine accessories[J].Journals of Propulsion Technology,2013,34(8):1101-1107.(in Chinese) [20] ARNOLD S P E.Lessons learned to improve HCF demonstration tests[R].RTO-MP-AVT-121,2005:20.1-20.12.
点击查看大图
计量
- 文章访问数: 761
- HTML浏览量: 8
- PDF量: 1138
- 被引次数: 0