文献类型：期刊文献

中文题名：循环热机载荷作用下航空涡轮盘蠕变疲劳寿命预测

英文题名：Creep fatigue life prediction of aero-engine turbine disc under cyclic thermal load

作者：陈克明[1];田若洲[1];郭素娟[1];王润梓[1];张成成[2];陈浩峰[1];张显程[1];涂善东[1]

机构：[1]华东理工大学承压系统与安全教育部重点实验室,上海200237;[2]中国航发商用发动机有限责任公司,上海201100

年份：2022

卷号：43

期号：5

起止页码：328

中文期刊名：航空学报

外文期刊名：Acta Aeronautica et Astronautica Sinica

收录：CSTPCD;;EI(收录号：20222512254966);Scopus;北大核心:【北大核心2020】；CSCD:【CSCD2021_2022】；

基金：国家自然科学基金(11872181);上海市自然科学基金(18ZR1408900)。

语种：中文

中文关键词：航空涡轮盘;蠕变疲劳;寿命预测;GH4169;温度场

外文关键词：aviation turbine disk;creep fatigue;life prediction;GH4169;temperature field

摘要：基于循环弹塑性本构模型(考虑Chaboche随动强化演化律)、应变强化蠕变本构模型和对先进蠕变-疲劳损伤模型的结构拓展,建立了预测航空涡轮盘在循环热-机蠕变-疲劳载荷谱下的蠕变-疲劳行为的数值流程,实现了对某型涡轮盘的蠕变-疲劳寿命的模拟和设计。结果表明:该涡轮盘在4 h巡航的服役过程中蠕变-疲劳损伤危险区主要集中在榫槽底部,靠近榫槽的盘缘和盘体的形状突变区;榫槽端由于温度较高,应力集中程度也高,总损伤最大,呈现蠕变损伤主导的情况;盘心区温度较低主要以疲劳损伤为主;涡轮盘最大损伤随单次飞行的巡航时间而增加,并逐渐从疲劳主导过渡到蠕变主导。论文研究成果可为航空发动机涡轮盘的长寿命、高可靠设计提供重要参考。
On the cyclic elastoplastic constitutive model(considering the Chaboche nonlinear kinematic hardening rule),the strain-hardening creep constitutive model and the reasonable expansion of the advanced creep-fatigue damage model.The creep-fatigue damage of a certain type of turbine disk was simulated and predicted.The results show that during the service of 4 h cruise,the most dangerous zone of creep and fatigue damage of the turbine disc mainly at the bottom of the tenon groove,the disc edge close to the tongue and groove and the shape mutation area of the disc.Maximum damage is found at the end of the tenon groove,and the damage dominated by creep.The damage pattern is dominated by fatigue in the core area of the disk with lower temperature.The maximum damage of the turbine disc increases with the cruise time of a single flight,gradually from fatigue dominance condition to creep dominance condition.Research can provide important reference for the long-life and high-reliability design of aero-engine turbine disc.