涡轮叶片耦合疲劳寿命预测与试验验证

由于; 徐健; 燕群; 张伟; 郭定文; 黄太誉

doi:10.13224/j.cnki.jasp.20210019

涡轮叶片耦合疲劳寿命预测与试验验证

doi: 10.13224/j.cnki.jasp.20210019

中国飞机强度研究所航空声学与振动航空科技重点实验室，西安 710065

详细信息

作者简介:
由于（1989-），男，高级工程师，硕士，主要从事航空发动机强度分析与试验研究。

中图分类号: V235.13
计量
- 文章访问数: 767
- HTML浏览量: 231
- PDF量: 218
- 被引次数: 0
出版历程
- 收稿日期: 2021-01-14
- 刊出日期: 2022-05-28

Combined fatigue life prediction and experiment verification for turbine blade

Laboratory of Aeronautical Acoustics and Vibration，Aircraft Strength Research Institute of China，Xi'an 710065，China

摘要

摘要: 为了解决涡轮转子叶片在温度、离心力和气动/噪声联合载荷作用下的疲劳强度问题，开展了高低周复合载荷谱分解方法和基于高低周载荷的全时域蠕变损伤累积模型研究，提出了同时考虑蠕变损伤、低周疲劳损伤和高周疲劳损伤的耦合疲劳寿命预测方法。同时，通过正交载荷解耦和耦合载荷协调加载控制等关键技术的应用，开发了高温环境下的高低周复合疲劳试验平台。最终，基于设计的涡轮叶片模拟件，完成了耦合疲劳寿命预测和试验验证。结果表明：模拟试件的耦合疲劳寿命试验结果分散系数为1.01，耦合疲劳寿命的预测结果与试验结果偏差小于24%，从而验证了疲劳寿命预测模型的正确性，为我国航空发动机热端部件的疲劳强度设计和验证提供了有效的技术途径。
- 涡轮转子叶片 /
- 高低周复合载荷 /
- 蠕变损伤累积 /
- 耦合疲劳寿命 /
- 正交载荷解耦 /
- 协调加载控制
Abstract: In order to solve the fatigue strength problems of turbine rotor blade under the combined loads of temperature,centrifugal force and aerodynamic/acoustic,the decomposition method of a high-low cycle complex load spectrum and the full-time domain creep damage cumulative model based on the high-low cycle complex load were investigated.The combined fatigue life prediction method considering simultaneously the fatigue damage of creep,low cycle and high cycle was proposed.Meanwhile,the high-low cycle complex fatigue experiment platform was developed through application of the critical technologies,such as orthogonal loads decoupling and coordinated loading control of the complex load.Finally,taking a simulation specimen of a turbine blade as the research object,the combined fatigue life prediction and experiment verification were accomplished.Results showed that the scatter factor of experiment result of combined fatigue life was 1.01,and the deviation between the prediction result and the experiment result was less than 24%.The validity of fatigue life prediction model was verified,providing an effective technical approach to fatigue strength design and validation for aero-engine hot-end components.
- turbine rotor blade /
- high-low cycle complex load /
- creep damage cumulative /
- combined fatigue life /
- orthogonal loads decoupling /
- coordinated loading control

HTML

参考文献(19)

[1]	陶春虎,钟培道,王仁智,等.航空发动机转动部件的失效与预防[M].北京:国防工业出版社,2008.
[2]	王红,左华付,何训,等.某型航空发动机第三级涡轮叶片失效分析[J].失效分析与预防,2007,2（1）:24-28.
[3]	COWLES B A.High cycle fatigue in aircraft gas turbines-an industry perspective[J].International Journal of fracture,1996,80（2）:147-163.
[4]	WESER S,GAMPE U,RADDATZ M,et al.Advanced experimental and analytical investigations on combined cycle fatigue （CCF） of conventional cast and single-crystal gas turbine blades[R].ASME Paper GT2011-45171,2011.
[5]	陈立杰,冶铁强,谢里阳.涡轮叶片蠕变-疲劳交互作用下寿命预测方法综述[J].航空制造技术,2004,47（12）:61-64,84.
[6]	高靖云,张成成,侯乃先,等.考虑应力松弛的单晶涡轮叶片蠕变疲劳寿命预测[J].航空动力学报,2016,31（3）:539-547.
[7]	ROGGE T,BERGER R,POHLE L,et al.Efficient structural analysis of gas turbine blades[J].Aircraft Engineering and Aerospace Technology,2016,90（9）:1305-1316.
[8]	李骏,宋友辉,刘汉斌,等.涡轮叶片-榫头-轮盘的蠕变与低循环疲劳寿命预测[J].推进技术,2015,36（11）:1699-1704.
[9]	ZHU Shunpeng,YUE Peng,YU Zhengyong.A combined high and low cycle fatigue model for life prediction of turbine blades[J].Materials,2017,10（7）:698-712.
[10]	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.
[11]	ZHENG X,ENGLER-PINTOJr .C C,SU X,et al.Modeling of fatigue damage under superimposed high-cycle and low-cycle fatigue loading for a cast aluminum alloy[J].Materials Science and Engineering A,2013,560（10）:792-801.
[12]	HAN Lei,HUANG Dawei,YAN Xiaojun,et al.Combined high and low cycle fatigue life prediction model based on damage mechanics and its application in determining the aluminized location of turbine blade[J].International Journal of Fatigue,2019,127（5）:120-130.
[13]	彭立强,王健.涡轮叶片高温多轴低周疲劳/蠕变寿命研究[J].航空动力学报,2009,24（7）:1549-1555.
[14]	HU Dianyin,WANG Rongqiao.Combined fatigue experiments on full scale turbine components[J].Aircraft Engineering and Aerospace Technology,2013,385（1）:4-9.
[15]	SHI D,LI Z,YANG X.Accelerated LCF-creep experimental methodology for durability life evaluation of turbine blade[J].Fatigue & Fracture of Engineering Materials & Structures,2018,41（5）:1196-1207.
[16]	THIELE M,WESER S,GAMPE U,et al.Advancement of experimental methods and cailletaud material model for life prediction of gas turbine blades exposed to combined cycle fatigue[R].ASME Paper GT2012-68452,2012.
[17]	侯静泳,蔡肇云,屠一鹤.TC-11钛合金高低周复合疲劳及损伤累积研究[J].航空动力学报,1992,7（2）:135-138.
[18]	《中国航空材料手册》编委会.中国航空材料手册:第2卷[M].北京:中国标准出版社,2001.
[19]	由于,张伟,燕群,等.基于高低周复合疲劳试验技术的叶片失效故障复现[J].推进技术,2020,41（5）:1130-1137.