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Experimental investigation of an oscillating compressor cascade in the case of aerodynamic mistuning
Citation key malzacher_diss_2021_en
Author Leonie Malzacher
Year 2021
DOI 10.14279/depositonce-11340
Location Berlin
Month February
Editor DepositOnce - Institutional Repository for Research Data and Publications of TU Berlin
How Published Creative Commons Attribution 4.0 International CC BY 4.0
School Technische Universit├Ąt Berlin
Abstract An experimental investigation has been carried out at an oscillating compressor cascade at the chair for Aero Engines of the Technische Universit at Berlin in Germany. The investigation focuses on the effect of aerodynamic mistuning on aeroelastic stability in a compressor cascade. Aerodynamic mistuning can occur due to manufacturing errors, blade mounting or repair and alters geometrical parameters of the flow passage. It influences the blade surface pressure distribution and can degrade the aeroelastic response of the system. In order to investigate the flutter behavior in the case of aerodynamic mistuning, the aerodynamic response of a mistuned oscillating compressor cascade has been studied. In the measurement section of the test facility, the blades are forced to oscillate sinusoidally in a pitching mode for a wide range of interblade phase angles at different reduced frequencies. The aerodynamic mistuning is introduced by a blade stagger-to-stagger angle variation. Four different mistuning patterns are investigated: one-blade mis-staggering, alternating mis-staggering, random mis-staggering and cases in which all blades in the cascade feature a constant stagger angle alteration. The test facility is equipped with steady and unsteady measurement devices. Firstly, the base flow characteristic is presented for different Mach and Reynolds numbers. The aerodynamic response is acquired by means of unsteady blade surface pressure and strain gauge measurements. The results suggest that aerodynamic mistuning stabilizes or destabilizes the system depending on the nature of the mistuning pattern. For a positive change in stagger angle for the one-blade and alternating pattern, the damping characteristic is maintained for the system. That is, the same unstable interblade phase angle remains unstable compared to the baseline case. For the negative stagger angle variations, the aerodynamic damping turns negative for one interblade phase angle, indicating instability compared to the baseline case. For large negative stagger angle variations of all blades of the cascade, the amplitude of the damping curve is especially affected and dictates the severity of these stability regions. In the past, most of the mistuning research was dedicated to structural blade-to-blade alteration e.g. changes in mass, stiffness and damping, influencing the eigenfrequencies. Thus, the present work contributes to extent the physical understanding of aerodynamic mistuning in a traveling wave test setup and characterizes the underlying mechanisms.
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