Thermal Residual Stress Relaxation and Distortion in Surface Enhanced Gas Turbine Engine Components

摘要

Compressive residual stresses are often deliberately induced in the surfaces of turbine engine components using a variety of surface enhancement methods to improve fatigue life. Thermal stress relaxation can occur in both the Ti and Ni alloys used in compressor and turbine stages Nonuniform relaxation of the compressive layer can cause distortion of the critical aerodynamics shapes of thin blades potentially effecting engine performance.