Automatized turbomachinery map generation and aeroelastic Analysis. Part 1: Steady fluid structure coupling and flutter analysis

Abstract

Many aspects of turbomachinery aeroelasticity are repetitive tasks with only slight parameter changes. These tasks have to be performed for many different operating conditions and different boundary conditions (flight condition, mode shapes, inter-blade phase angle/nodal diameters). To avoid user-based faults, mistakes, errors and to reduce manual work, a highly-automated toolchain for aeroelastic investigations of turbomachinery components has been developed at the DLR-Institute of Aeroelasticity. There was a high emphasis on generalizing the aspects of the computations.

The automated toolchain enables the user to concentrate more on the actual case setup and the phenomena to-be-investigated.

This part of the report focuses on to current implementation status for steady computations (incl. steady FSC), modal analysis and flutter analysis of isolated blade rows with the energy method.

This report intends to clarify the toolchain's usage and support future developers in an efficient implementation of their program parts.