某涡轴发动机涡轮叶片尾缘孔的蠕变-疲劳寿命预测方法

钱正明; 李概奇; 米栋; 艾兴

doi:10.13224/j.cnki.jasp.20210130

某涡轴发动机涡轮叶片尾缘孔的蠕变-疲劳寿命预测方法

doi: 10.13224/j.cnki.jasp.20210130

中国航空发动机集团有限公司湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
钱正明（1987-），男，高级工程师，硕士，主要从事航空发动机强度设计及多学科设计等方面的研究。

通讯作者:
李概奇（1966-），男，研究员，博士，主要从事航空发动机设计研究。E-mail：qsy160905@163.com

中图分类号: V215
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出版历程
- 收稿日期: 2021-03-24
- 刊出日期: 2021-11-28

Creep-fatigue life prediction method of tail edge holes in turbine blade for a turboshaft engine

Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要: 针对某涡轴发动机的涡轮叶片，建立了考虑应力松弛的蠕变-疲劳寿命分析方法。通过在黏塑性理论框架内耦合蠕变损伤，对某高温合金的非线性蠕变变形进行了数值模拟。结果表明：基于对某涡轮叶片的弹塑性-蠕变分析研究，明确了叶片上前缘和尾缘等关键部位的蠕变损伤及其演化规律，也为确定叶片上的局部危险点提供了一种方法。该模型针对弹塑性应力应变曲线计算误差小于5%，而针对蠕变曲线的模拟精度则处于材料蠕变变形固有属性分散范围内。借助于线性损伤累积寿命理论，分析得到了某涡轮叶片尾缘孔局部考虑了应力松弛的蠕变-疲劳寿命，从而为叶片寿命评价提供了更为合理、工程化应用更好的方法。
- 疲劳 /
- 蠕变 /
- 寿命预测 /
- 涡轮叶片 /
- 损伤
Abstract: A creep-fatigue life analysis method considering stress relaxation was established for turbine blade in a turboshaft engine.The nonlinear creep deformation of a superalloy was predicted by coupling creep damage in the framework of viscoplastic theory.The results revealed that based on the elastic-plastic creep analysis of a turbine blade，the creep damage and its evolution law of the leading edge and trailing edge of the blade were clarified，and a method was provided for determining the local dangerous points on the blade.The calculation error of the model for the elastic-plastic stress-strain curve was less than 5%，while the simulation accuracy for the creep curve was within the dispersion range of the inherent properties of material creep deformation.With the help of the linear damage cumulative life theory，the creep-fatigue life of the trailing edge hole of a turbine blade considering the stress relaxation was obtained，providing a more reasonable and better engineering application method for the blade life evaluation.
- fatigue /
- creep /
- life prediction /
- gas turbine blade /
- damage

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