A time-accurate aeroelastic solver was developed in order to compute the unsteady flow field around an oscillating cascade. The implemented method is based on the unsteady Traf code, which was extended to flutter computations. A dual time-stepping technique is employed to integrate the unsteady solution on a moving grid. This method was validated for turbine blade applications by computing the aeroelastic behaviours of the 4th and 11th three-dimensional Standard Configurations. For each test case, the aeroelastic solution was computed for various values of inter-blade phase angle and compared to experimental data. The results show a good agreement, even when non-linear effects such as shock waves and boundary layer separation are present.
A Time-Accurate 3D Method for Turbomachinery Blade Flutter Analysis / L. Pinelli; F. Poli; A. Arnone; C. Schipani. - ELETTRONICO. - (2009), pp. 1-9. (Intervento presentato al convegno 12th International Symposium on Unsteady Aerodynamics, Aeroacustics and Aeroelasticity of Turbomachines (ISUAAAT) tenutosi a London, UK nel 1-4 September 2009).
A Time-Accurate 3D Method for Turbomachinery Blade Flutter Analysis
PINELLI, LORENZO;POLI, FRANCESCO;ARNONE, ANDREA;
2009
Abstract
A time-accurate aeroelastic solver was developed in order to compute the unsteady flow field around an oscillating cascade. The implemented method is based on the unsteady Traf code, which was extended to flutter computations. A dual time-stepping technique is employed to integrate the unsteady solution on a moving grid. This method was validated for turbine blade applications by computing the aeroelastic behaviours of the 4th and 11th three-dimensional Standard Configurations. For each test case, the aeroelastic solution was computed for various values of inter-blade phase angle and compared to experimental data. The results show a good agreement, even when non-linear effects such as shock waves and boundary layer separation are present.
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