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Experimental Investigation of the Aeordynamic Stability of an Annular Compressor Cascade Performing Tuned Pitching Oscillations in Transonic Flow

Hennings, H. and Belz, J. (1999) Experimental Investigation of the Aeordynamic Stability of an Annular Compressor Cascade Performing Tuned Pitching Oscillations in Transonic Flow. In: American Society of Mechanical Engineers, ASME Paper 99-GT-407, pp. 1-8. ASME Turbo Expo '99, Indianapolis, June 7-10, 1999.

Full text not available from this repository.

Abstract

A prerequisite for aeroelastic stability investigations on vibrating compressor cascades is the detailed knowledge of the unsteady aerodynamic loads acting on the blades. In order to obtain precise insight into the aerodynamic damping of a vibrating blade assembly, a basic experiment was performed where unsteady pressure distributions were measured for subsonic and transonic flow conditions. The experiments were performed on a non-rotating, two-dimensional section of a compressor cascade in an annular test facility. The cascade consists of 20 blades (NACA3506 profile) mounted on elastic spring suspensions. In order to measure the unsteady pressure distribution, the cascade was set to tuned pitching oscillations (travelling wave modes). Each blade was driven to controlled harmonic torsional motions around midchord by a magnetic excitation system and by inductive displacement probes which measure the feedback signal of the motion. Steady and unsteady pressures were measured by steady pressure taps and piezo-electric pressure transducers, respectively. The measurement of the unsteady aerodynamic response to a shock vibrating on the suction side of the blades was enabled by a dense spacing of transducers in this region The global aeordynamic stability is assessed by a damping coefficient evaluated from the out-of-phase parts of the unsteady moment coefficients and by the contributions from the local work coefficient, using the measured pressure data.

Item URL in elib:https://elib.dlr.de/14159/
Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=1999,
Title:Experimental Investigation of the Aeordynamic Stability of an Annular Compressor Cascade Performing Tuned Pitching Oscillations in Transonic Flow
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hennings, H.UNSPECIFIEDUNSPECIFIED
Belz, J.UNSPECIFIEDUNSPECIFIED
Date:1999
Journal or Publication Title:American Society of Mechanical Engineers
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Volume:ASME Paper 99-GT-407
Page Range:pp. 1-8
Status:Published
Keywords:aeroelasticity, compressor cascade, annular windtunnel, transonic flow, pitching oscillations, unsteady aerodynamics, experimental aerodynamic stability investigations, local work coefficient
Event Title:ASME Turbo Expo '99, Indianapolis, June 7-10, 1999
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L TT - Triebwerkstechnologien
DLR - Research theme (Project):L - Fan and Compressor Technologies (old)
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: DLR-Beauftragter, elib
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 21:29

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