Experimental Investigation of the Influence of Local Flow Features on the Aerodynamic Damping of an Oscillating Blade Row
2014 (English)Licentiate thesis, monograph (Other academic)
The general trend of efficiency increase, weight and noise reduction has derived in the design of more slender, loaded, and 3D shaped blades. This has a significant impact on the stability of fan, and low pressure turbine blades, which are more prone to aeroelastic phenomena such as flutter. The flutter phenomenon is a self-excited, self-sustained unstable vibration produced by the interaction of flow and structure. These working conditions will induce either blade overload, or High Cycle Fatigue (HCF) produced by Limited Cycle Oscillation (LCO).
The main objectives of the present work are on the investigation of the aeroelastic properties of a high-lift low-pressure in the light of the local flow features present in such profiles, in nominal and extreme off-design conditions both in high and low subsonic Mach number, for three dif-ferent rigid body modes. In addition, the validity of the linearity assump-tion of the influence coefficient technique has also been investigated, in order to expand the understanding of the physical limits of this assumption.
This work has been designed as experimental investigation in the influence coefficient domain focused on a high-lift low-pressure turbine designed by ITP within the framework of the European FP7 project FU-TURE. These experiments have been carried out in the Aeroelastic test rig (AETR), at KTH Stockholm, which consist of an instrumented annular sector cascade with a single oscillating blade. The results acquired have been supported by numerical results provided by a non-propietary commercial software package (ANSYS CFX).
The results suggest that the typical three-dimensional effects associated secondary flow features and tip leakage flows have a significant influence on the aeroelastic performance and the cascade stability. However the major influence appears as a consequence of the separation surface on the pressure side which appears at extreme off-design operating conditions. The contribution to stability of this local feature depend on the oscillation mode showing for the axial and torsion mode a neutral stability contribution, which is directly associated with the geometrical properties of the cascade. However, on the circumferential mode this separation surface has a stabilizing effect much more independent of the blade geometry.
The study of the linearity assumption of the influence coefficient domain has revealed, that an apparent linear relation between the integrated unsteady response and the vibrational amplitude, does not necessary imply that the local unsteady response is linear with respect to the oscillation amplitude. The results also suggest that the validity of the linearity as-sumption is more sensitive to high oscillation amplitudes at high Mach conditions.
Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2014. , 126 p.
TRITA-KRV, ISSN 1100-7990 ; 14:02
Turbomachinery, Aeroelasticity, Flutter, Experimental Aerodynamics, CFD, Local Flow Features, Influence Coefficient, Linearity Assumption
Research subject Aerospace Engineering
IdentifiersURN: urn:nbn:se:kth:diva-145179ISBN: 978-91-7595-145-4OAI: oai:DiVA.org:kth-145179DiVA: diva2:721826
2014-06-09, ITM_EGI_EKV_LEARNING_THEATRE, Brinellvägen 68, KTH, Stockholm, 11:00 (English)
Paniagua, Guillermo, Associate Professor
Fransson, Torsten, ProfessorVogt, Damian, Professor
QC 201406092014-06-092014-05-142014-06-09Bibliographically approved