PREDICTING RESIDUAL-STRESSES IN GAS-TURBINE COMPONENTS

This article describes work carried out by a major aircraft-engine bui lder and one of its suppliers to validate the numerical prediction of heat-treatment-induced residual stresses. For verification, the projec t used a large-scale, nickel-based superalloy forging; calculated stre sses are compared to those measured using a hole-drilling technique. E ven though the analyses were conducted by both companies using differe nt software, the results tie closely with the measurements.