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AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: EXPERIMENTAL RESULTS

Chenaux, Virginie Anne and Ott, Peter and Zanker, Achim (2015) AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: EXPERIMENTAL RESULTS. In: Proceedings of the ASME Turbo Expo. ASME. ASME Turbo Expo Konferenz 2015, 15.-19. Juni 2015, Montreal, Kanada.

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Abstract

A reliable determination of the unsteady aerodynamic loads acting on the blades is essential to predict the aeroelastic stability of vibrating compressor cascades with accuracy. At transonic flow conditions, the vibration of the shock may change the blade aeroelastic behavior. Numerical tools still have difficulties to capture the physics associated to this effect. In order to increase the prediction’s accuracy, high quality experimental data at high spatial resolution is therefore required to enable the calibration and validation of these tools. Within the frame of the European project FUTURE, experimental aeroelastic investigations were performed on a transonic compressor cascade in the Non-Rotating Annular Test Facility at EPFL. Associated to the measurements, the numerical flutter prediction procedure was applied. This paper focuses on the experimental results. The experimental database gained during the project is presented and aims at helping the aeroelastic community to develop and improve their flutter prediction capabilities. The test model consists of twenty prismatic blades. Each blade of the cascade assembly was mounted on an elastic spring element enabling harmonic bending vibrations in the twenty possible cascade’s travelling wave modes. Large efforts were made to improve the measuring techniques and to provide high quality data at relatively high spatial resolution. For various sub- and transonic flow conditions, steady-state and unsteady blade surface pressure distributions were measured to evaluate the local contributions to the blade stability in terms of local aerodynamic work. The blade global aerodynamic stability is determined applying an integration of all unsteady pressure signals measured over the airfoil.

Item URL in elib:https://elib.dlr.de/97923/
Document Type:Conference or Workshop Item (Speech)
Title:AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: EXPERIMENTAL RESULTS
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Chenaux, Virginie Annevirginie.chenaux (at) dlr.deUNSPECIFIED
Ott, Peterpeter.ott (at) epfl.chUNSPECIFIED
Zanker, Achimachim.zanker (at) alumni.epfl.chUNSPECIFIED
Date:15 June 2015
Journal or Publication Title:Proceedings of the ASME Turbo Expo
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Publisher:ASME
Status:Published
Keywords:aeroelasticity, compressor cascade, annular cascade, aerodynamic damping, unsteady pressures, experimental investigation.
Event Title:ASME Turbo Expo Konferenz 2015
Event Location:Montreal, Kanada
Event Type:international Conference
Event Dates:15.-19. Juni 2015
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Virtual Engine and Validation methods
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Aeroelastic Experiments
Deposited By: Chenaux, Virginie
Deposited On:13 Oct 2015 09:27
Last Modified:09 Feb 2018 13:03

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