Experimental and numerical assessment of the aeroelastic stability of blade pair packages

Vega Coso, Almudena and Corral Garcia, Roque and Zanker, Achim and Ott, Peter (2014). Experimental and numerical assessment of the aeroelastic stability of blade pair packages. In: "Turbo Expo 2014: Turbine Technical Conference and Exposition", 16-20 jun 2014, Düsseldorf, Alemania. ISBN 978-0-7918-4577-6. pp. 176-188.

Description

Title: Experimental and numerical assessment of the aeroelastic stability of blade pair packages
Author/s:
  • Vega Coso, Almudena
  • Corral Garcia, Roque
  • Zanker, Achim
  • Ott, Peter
Item Type: Presentation at Congress or Conference (Article)
Event Title: Turbo Expo 2014: Turbine Technical Conference and Exposition
Event Dates: 16-20 jun 2014
Event Location: Düsseldorf, Alemania
Title of Book: ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
Date: 2014
ISBN: 978-0-7918-4577-6
Volume: 7B
Subjects:
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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Abstract

The stabilizing effect of grouping rotor blades in pairs has been assessed both, numerically and experimentally. The bending and torsion modes of a low aspect ratio high speed turbine cascade tested in the non-rotating test facility at EPFL (Ecole Polytechnique Fédérale de Lausanne) have been chosen as the case study. The controlled vibration of 20 blades in travelling wave form was performed by means of an electromagnetic excitation system, enabling the adjustement of the vibration amplitude and inter blade phase at a given frequency. Unsteady pressure transducers located along the blade mid-section were used to obtain the modulus and phase of the unsteady pressure caused by the airfoil motion. The stabilizing effect of the torsion mode was clearly observed both in the experiments and the simulations, however the effect of grouping the blades in pairs in the minimum damping at the tested frequency was marginal in the bending mode. A numerical tool was validated using the available experimental data and then used to extend the results at lower and more relevant reduced frequencies. It is shown that the stabilizing effect exists for the bending and torsion modes in the frequency range typical of low-pressure turbines. It is concluded that the stabilizing effect of this configuration is due to the shielding effect of the pressure side of the airfoil that defines the passage of the pair on the suction side of the same passage, since the relative motion between both is null. This effect is observed both in the experiments and simulations.

More information

Item ID: 37667
DC Identifier: http://oa.upm.es/37667/
OAI Identifier: oai:oa.upm.es:37667
Official URL: http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1908508
Deposited by: Memoria Investigacion
Deposited on: 05 Feb 2016 11:24
Last Modified: 05 Feb 2016 11:24
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