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research-article

A LOW SPEED COMPRESSOR TEST RIG FOR FLUTTER INVESTIGATIONS

[+] Author and Article Information
Leonie Malzacher

Department of Aeronautics and Astronautics, Technische Universität Berlin, Marchstr. 12-14, 10587 Berlin, Germany
leonie.malzacher@tu-berlin.de

Silvio Geist

Department of Aeronautics and Astronautics, Technische Universität Berlin, Marchstr. 12-14, 10587 Berlin, Germany
silvio.geist@hsu-hh.de

Valentina Motta

Department of Aeronautics and Astronautics, Technische Universität Berlin, Marchstr. 12-14, 10587 Berlin, Germany
valentina.motta@ilr.tu-berlin.de

Dieter Peitsch

Department of Aeronautics and Astronautics, Technische Universität Berlin, Marchstr. 12-14, 10587 Berlin, Germany
dieter.peitsch@ilr.tu-berlin.de

Holger Hennings

German Aerospace Center, Institute of Aeroelasticity, Bunsenstraße 10, 37073 Göttingen, Germany
holger.hennings@dlr.de

1Corresponding author.

ASME doi:10.1115/1.4041817 History: Received August 23, 2018; Revised October 12, 2018

Abstract

A test facility for aereolastic investigations has been set up at the chair of Aero Engines at the Technische Universität Berlin. The test rig provides data for tool and code validation and is used for basic aeroelastic experiments. It is a low speed wind tunnel which allows free and controlled flutter testing. The test section contains a linear cascade with eleven compressor blades. Nine of them are elastically suspended. The paper presents a detailed description of the test facility, results to evaluate the overall flow quality along side an aeroelastic model to predict the flutter velocity and critical interblade phase angles. Furthermore, chordwise pressure distributions, measured with traveling wave mode experimental tests, are presented. These measurements have been carried out for a wide ranges of interblade phase angles and have been compared to numerical results. Hot-wire anemometry has been applied to examine the inlet flow for several Mach- and Reynolds numbers. The results show small turbulence intensities. The blade surface pressure distribution and the flow field of the blade's suction and pressure side has been obtained by oil flow visualization.

Copyright (c) 2018 by ASME
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