氧化损伤对航空发动机涡轮叶片裂纹扩展影响OA

Oxidative damage and cracks are inevitable during the service process of turbine blades.Predicting crack behavior and the impact on oxidation damage are of great significance for service safety and life management.Aiming at the problem of oxidation damage and crack of high pressure turbine blades of aero-engine in high temperature environment for a long time,the crack growth rates of normal and post oxidation damaged specimens were obtained by crack growth tests of Compact Tension(CT)specimens at 850℃;The Paris model was used to consider the crack growth with oxidation damage,and the effect of oxidation damage on the crack growth rate was compared.This article takes a high-pressure turbine blade of an aero-engine as an example,focusing on the influence of oxidative damage on the crack growth stage.The crack growth life of the turbine blade with and without oxidation damage was analyzed and compared using the software of ANSYS and Franc3D.The results show that under the influence of oxidation damage,the average cycle life of blade leading edge cracks decreases to 44.02%without oxidation damage,and the average cycle life of blade trailing edge cracks decreases to 50.22%without oxidation damage.It is of great practical significance for providing a basic reference for the life assessment of turbine blades under actual service environment and working conditions,as well as correctly evaluating materials,predicting the service life and design strength of engineering hot end components in other practical engineering.