[+] Author and Article Information
Leonie Malzacher

Marchstr. 12--14 Berlin, Deutschland (DEU) 10587 Germany leonie.malzacher@tu-berlin.de*

Valentina Motta

via La Masa 34 Milano, 20156 Italy valentina.motta@polimi.it

Christopher Schwarze

Marchstraße 12 - 14 Berlin, 10587 Germany christopher.schwarze@lht.dlh.de

Dieter Peitsch

Marchstrasse 12-14 Berlin, 10587 Germany dieter.peitsch@tu-berlin.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received February 5, 2019; final manuscript received April 9, 2019; published online xx xx, xxxx. Assoc. Editor: Kenneth Hall.

*Address all correspondence to this author.

Present address: Lufthansa Technik AG, Weg beim Jäger 193, 22335 Hamburg.

ASME doi:10.1115/1.4043474 History: Received February 05, 2019; Accepted April 09, 2019


In this paper, the effect of aerodynamic mistuning on stability of a compressor cascade is studied. The experiments have been carried out at a low speed test facility of the Technische Universität Berlin. The test section contains a linear cascade with compressor blades that are forced to oscillate in sinusoidal pitching motion. The aerodynamic mistuning is realized by a blade-to-blade stagger angle variation, three mistuning patterns have been investigated: one-blade mis-staggering, alternating mis-staggering and random mis-staggering. Mis-staggering can have stabilizing or destsabilizing effect, but depends strongly on the amount of the detuning that alters the flow passage. For positive stagger angle variation for the one-blade and alternating mis-staggering, the trend of the damping curve was maintained, in the sense that the unstable interblade phase angles (IBPA) remained unstable. For negative stagger angle variation, one IBPA shifted from stable to unstable. For the random pattern only very moderate changes are observed. The cascade stability was not noticeably effected by the aerodynamic mistuning.

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