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Experimental investigation of an oscillating compressor cascade in the presence of a periodic unsteady inlet flow
- Scheme of the test facility for aeroelastic investigations with a mechanism to generate a periodic unsteady inlet flow
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- © TUB F1
Summary
In this project a contribution to the physical understanding of
low-frequency excitation with amplitudes on the unsteady blade
response will be made. The causes for such excitations are often not
predictable or can only be inadequately modeled, but can lead to
fatigue damage of compressor blades.
The experiments are
conducted at the test facility for aeroelastic investigations of the
chair for aero engines of TU Berlin. The measurement section of the
facility consists of a large-scale compressor cascade with eleven
blades. With stepper motors, nine of the blades can be forced to
vibrate in torsion and plunging mode. The modular character of the
facility permits the integration of a mechanism for generating a
periodic unsteady inlet low, which can be installed upstream of the
compressor cascade. In this way different excitation patterns can be
realized within the framework of the research project. The unsteady
aerodynamic blade response in the absence and presence of a
periodically unsteady inlet flow can be measured. Therefore, the
proposed basic experiment is capable of investigating how
low-frequency excitations with small amplitudes influence the blade
response. Through the variation of the parameters and a detailed
investigation of the phase between excitation and blade motion, it is
also assessed whether the response problem can be described with
linear theory.
The investigations will be performed by
means of state of the art technology. Hot wire measurement technology
will be used to characterize the periodic unsteady inflow. The
unsteady aerodynamic pressure distribution along the blade surface is
measured with piezoresistive pressure transducers and the vibration
frequency and amplitude with strain gauges.
Person of contact: M.Sc. Leonie Malzacher
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References
Experimental Investigation of an
Aerodynamically Mistuned Oscillating
Compressor
Cascade
L. Malzacher, C. Schwarze, V. Motta, D.
Peitsch
Journal of Turbomachinery, Volume 141, Issue 7, 071012 (9
pages), July 2019
DOI: 10.1115/1.4043474 [2]
A Low-Speed Compressor Test Rigfor Flutter
Investigations
L. Malzacher, S. Geist, D. Peitsch,
H. Hennings
Joumal of Turbomachinery, Volume 141, Issue 5, 051009
(12 pages), May 2019
DOI: 10.1115/1.4041817 [3]
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Contact
M.Sc. Liesbeth KonrathTel. +49 (0)30 314-25008
Institute for Aeronautics & Astronautics
Room F 004
e-mail query [5]
Website [6]
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