航空发动机涡轮部件蠕变失效风险分析

Creep Failure Risk Analysis of Aircraft Engine Turbine Components

建立了商用航空发动机典型部件蠕变风险分析方法,该方法在考虑蠕变本构的有限元计算的基础上,综合蠕变损伤计算、蠕变持久寿命预测及蒙特卡洛分析的方法,对高温高载荷耦合环境下的航空发动机典型部件蠕变失效风险进行了预测。同时,开发了蠕变风险计算程序,给出了蠕变风险计算流程,以商用航空发动机涡轮叶片为例开展了不同使用循环数下的蠕变失效风险计算。计算结果表明,该叶片设计构型在99.87%的可靠度下其蠕变寿命约为1150次循环。

A creep risk analysis method for typical components of commercial aircraft engines was established in this paper.Based on finite element calculation,combined with creep damage calculation,creep durability life prediction and Monte-Carlo analy⁃sis method,the creep failure risk of typical components of aircraft engine under high temperature and high load coupling environ⁃ment was predicted.At the same time,the creep risk calculation program was developed,and the creep risk calculation process was provided.Taking the commercial aircraft engine turbine blade as an example,the creep failure risk calculation under differ⁃ent life cycles was carried out.The analysis result indicated that the creep life of the certain turbine blade is about 1150 cycles with 99.87%reliability.