Motivation
The functionality, operational behavior and service life of highly stressed, safety-relevant aircraft engine components made of the nickel-based alloy Inconel 718, are largely determined by the manufacturing accuracy and the edge zone properties. Therefore, high demands are placed on finished turbine parts with regard to geometrical deviations as well as residual stresses and changes in the material microstructure in the edge zone. The adjustment of these component properties is usually determined by the final machining of forged and subsequently heat-treated semi-finished products. During machining and particularly in turning operations, due to the existing thermo-mechanical load collective, residual stresses are introduced near the edge zone, which are superimposed on the inherent residual stresses resulting in component distortion that is difficult to control. An accurate prediction of residual stresses and machining-related component distortion could be achieved by a cross-scale numerical modeling approach which leads to prevention of time-consuming and cost-intensive post-treatment or component rejection.
Objectives
Project Contents
Project partner
Laboratory for Machine Tools and Production Engineering (WZL)
Funding
Funded by German Research Society
