摘要
为提高船用燃气轮机涡轮盘的寿命设计水平,基于数值仿真方法对涡轮盘开展典型循环载荷作用下应力应变状态分析,并通过Morrow平均应力修正模型和SWT参数模型对涡轮盘裂纹萌生位置及寿命进行预测。在此基础上,进一步对涡轮盘高温合金材料开展不同温度下疲劳裂纹扩展试验,建立涡轮盘裂纹扩展速率模型,通过ANSYS软件和裂纹扩展程序仿真研究裂纹扩展寿命。结果表明:涡轮盘通气孔位置为裂纹萌生的危险位置,涡轮盘材料裂纹扩展速率随温度升高而明显增加,涡轮盘通气孔疲劳裂纹扩展寿命为18525次循环,研究结果可为燃气轮机涡轮盘损伤容限设计提供参考。
In order to improve the life design level of the turbine disk of marine gas turbine,the stress and strain state of the turbine disk under typical cyclic loading based on numerical simulation method was analyzed,and the location of crack initiation and life of the turbine disk were predicted by Morrow average stress correction model and SWT parameter model.On this basis,for the high temperature alloy materials used in the turbine disk,the fatigue crack growth tests at different temperatures were furtherly carried out,the crack growth rate model of the turbine disk was established,and the crack growth life was studied through the simulation of ANSYS software and crack growth program.The result shows that the vent hole of turbine disk is dangerous position for crack initiation,the crack growth rate of the turbine disk material increases significantly with the increase of temperature,and the fatigue crack growth lives of the vent hole are 18525 cycles.The research results can provide valuable references for the design of damage tolerance of gas turbine disk.
作者
林枫
梁晨
季晨
孙景国
LIN Feng;LIANG Chen;JI Chen;SUN Jingguo(No.703 Research Institute of CSSC,Harbin,China,Post Code:150078;National Key Laboratory of Marine Engine Science and Technology,Harbin,China,Post Code:150078)
出处
《热能动力工程》
北大核心
2025年第6期156-164,共9页
Journal of Engineering for Thermal Energy and Power
基金
国家重大科技专项(J2019-Ⅳ-0012-0055)
先进船舶发动机技术全国重点实验室基金资助。
关键词
燃气轮机
仿真分析
低周疲劳
裂纹扩展
疲劳寿命
gas turbine
simulation analysis
low cycle fatigue
crack growth
fatigue life
