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, and three mistuning patterns have been investigated: one-blade mis-staggering, alternating mis-staggering, and random mis-staggering. Mis-staggering can have a stabilizing or destsabilizing effect, but depends strongly on the amount of 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 (IBPAs) 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 affected by the aerodynamic mistuning.
Experimental Investigation of an Aerodynamically Mistuned Oscillating Compressor Cascade
Present address: Lufthansa Technik AG, Weg beim Jäger 193, 22335 Hamburg, Germany.
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 May 23, 2019. Assoc. Editor: Kenneth Hall.
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Malzacher, L., Schwarze, C., Motta, V., and Peitsch, D. (May 23, 2019). "Experimental Investigation of an Aerodynamically Mistuned Oscillating Compressor Cascade." ASME. J. Turbomach. July 2019; 141(7): 071012. https://doi.org/10.1115/1.4043474
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