Only one single integrated code is used: the modal equations of the structure part are solved within the fluid flow solver. No additional interpolation is required between fluid and structure data during the FSI computation, therefore reducing the computation time and increasing the accuracy.
Deformation field on stator blade of a compressor stage (Courtesy of TU Darmstadt)
With the turbomachinery design trends to reach more power with lighter components, the risk of flutter is becoming higher and is now a major concern in the design process. Flutter is a self-excited and self-sustained aeroelastic instability phenomenon that leads to fatigue and damage. It needs to be properly damped. Investigation of this phenomenon can be carried out by predicting the aerodynamic damping of the structure with the modal approach of FINE™/Turbo.
Magnitude of deformation (m) Rotor 67
- Simple and accurate approach for fluid structure interaction
- The structure eigenfrequencies and mode shapes are obtained during a pre-processing step
- Only one single integrated code is needed during the computation