Short Description

The development of an aero-engine is a complex and interdisciplinary process. The need of rapid and more precise predictions leads to the consideration of a wide variety of dependencies already at the pre-design phase. The usage of simplified generalized physics laws, underly well the scope of this goal and contribute to the creation of tools capable of achieving the desired level of detail. The mechanics discipline is an important step of the process, providing a first component design layout based on parametric studies. Such sophisticated methods can complement the other disciplines with a robust assessment of the structural integrity, component-based weight estimation and an initial evaluation of the component’s life. The major advantage of these methods is flexibility and therefore new concepts can easily be developed independently of the knowledge-based designs. This project focuses on the axial compressors and their interdependencies. Within the framework of this project for each major component of the compressor, blades, vanes, discs, casing, methods for the topology parametrization will be developed, while structural aspects such as stresses, mechanical and manufacturing limits, low and high cycle fatigue, creep, disc burst and casing containment will be evaluated.

[1] Jeschke, P., Kurzke, J., Schaber, R., and Riegler, C., 2004.“Preliminary Gas Turbine Design Using the Multidisciplinary Design System MOPEDS”. ASME Journal of Engineering for Gas Turbines and Power, 126.