A Low-Speed Compressor Test Rig for Flutter Investigations

Author:

Malzacher Leonie1,Geist Silvio1,Motta Valentina1,Peitsch Dieter1,Hennings Holger2

Affiliation:

1. Department of Aeronautics and Astronautics, Technische Universität Berlin, Marchstr. 12-14, Berlin 10587, Germany e-mail:

2. German Aerospace Center, Institute of Aeroelasticity, Bunsenstraße 10, Göttingen 37073, Germany e-mail:

Abstract

A test facility for aeroeolastic 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 alongside an aeroelastic model to predict the flutter velocity and critical interblade phase angles (IBPAs). Furthermore, chordwise pressure distributions, measured with traveling wave (TW) mode experimental tests, are presented. These measurements have been carried out for a wide range of IBPAs and have been compared to numerical results. Hot-wire anemometry has been applied to examine the inlet flow for several Mach numbers 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 sides have been obtained by oil flow visualization.

Publisher

ASME International

Subject

Mechanical Engineering

Reference22 articles.

1. Vogt, D., 2005, “Experimental Investigation of Three-Dimensional Mechanisms in Low-Pressure Turbine Flutter,” Ph.D. thesis, Royal Institute of Technology, Stockholm, Sweden.http://www.diva-portal.org/smash/get/diva2:7902/FULLTEXT01.pdf

2. System Mode Shapes in the Flutter of Compressor Blade Rows;J. Aeronaut. Sci.,1956

3. Aeroelastic Formulations for Turbomachines and Propellers,1988

4. Investigation of Blade Flutter in a Subsonic Turbine,1976

5. Urban, B., Stetter, H., and Vortmeyer, N., 2000, “Experimental Investigation of Shock-Induced Blade Oscillation at an Elastically Suspended Turbine Cascade in Transonic Flow,” ASME Paper No. 2000-GT-378.10.1115/2000-GT-0378

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