Physics of Vibrating Airfoils at Low Reduced Frequency

Vega Coso, Almudena and Corral Garcia, Roque (2013). Physics of Vibrating Airfoils at Low Reduced Frequency. In: "ASME Proceedings | Aerodynamic Excitation and Damping (With Turbomachinery)", June 3-7, 2013, San Antonio, Texas, USA. ISBN 978-0-7918-5527-0. pp. 176-190.


Title: Physics of Vibrating Airfoils at Low Reduced Frequency
  • Vega Coso, Almudena
  • Corral Garcia, Roque
Item Type: Presentation at Congress or Conference (Article)
Event Title: ASME Proceedings | Aerodynamic Excitation and Damping (With Turbomachinery)
Event Dates: June 3-7, 2013
Event Location: San Antonio, Texas, USA
Title of Book: ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
Date: June 2013
ISBN: 978-0-7918-5527-0
Volume: 7B
Faculty: E.T.S.I. Aeronáuticos (UPM)
Department: Fundamentos Matemáticos de la Tecnología Aeronáutica [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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The unsteady aerodynamics of low pressure turbine vibrating airfoils in flap mode is studied in detail using a frequency domain linearized Navier-Stokes solver. Both the travelling-wave and influence coefficient formulations of the problem are used to highlight key aspects of the physics and understand different trends such as the effect of reduced frequency and Mach number. The study is focused in the low-reduced frequency regime which is of paramount relevance for the design of aeronautical low-pressure turbines and compressors. It is concluded that the effect of the Mach number on the unsteady pressure phase can be neglected in first approximation and that the unsteadiness of the vibrating and adjacent airfoils is driven by vortex shedding mechanisms. Finally a simple model to estimate the work-per-cycle as a function of the reduced frequency and Mach Number is provided. The edge-wise and torsion modes are presented in less detail but it is shown that acoustic waves are essential to explain its behaviour. The non-dimensional work-per-cycle of the edge-wise mode shows a large dependence with the Mach number while in the torsion mode a large number of airfoils is needed to reconstruct the work-per-cycle departing from the influence coefficients.

Funding Projects

Government of SpainDPI2009-14216UnspecifiedUnspecifiedUnspecified

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Item ID: 37666
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Deposited by: Memoria Investigacion
Deposited on: 05 Feb 2016 17:54
Last Modified: 05 Feb 2016 17:54
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