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Research Papers

Experimental Investigation of an Aerodynamically Mistuned Oscillating Compressor Cascade

[+] Author and Article Information
Leonie Malzacher

Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14, 10587 Berlin, Germany
e-mail: leonie.malzacher@tu-berlin.de

Christopher Schwarze

Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14, 10587 Berlin, Germany
e-mail: christopher.schwarze@lht.dlh.de

Valentina Motta

Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14, 10587 Berlin, Germany
e-mail: valentina.motta@polimi.it

Dieter Peitsch

Department of Aeronautics and Astronautics,
Technische Universität Berlin,
Marchstr. 12-14, 10587 Berlin, Germany
e-mail: dieter.peitsch@tu-berlin.de

1Corresponding author.

2Present 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.

J. Turbomach 141(7), 071012 (May 23, 2019) (9 pages) Paper No: TURBO-19-1027; 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, 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.

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References

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Figures

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Fig. 1

Outline of the measurement section

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Fig. 2

Cascade geometrical parameters

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Fig. 3

Pressure tap distribution on the blade surface

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Fig. 4

Variation of real and imaginary parts of pressure difference coefficient; IBPA σ = 0 deg; reduced frequency ω* = 0.144

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Fig. 5

Steady pressure coefficient distribution on the cascade central blade: (a) one-blade mis-staggering configuration, (b) alternating mis-staggering configuration, and (c) random mis-staggering configuration

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Fig. 6

Variation of magnitude and phase angle of pressure difference coefficient Δcp with interblade phase angle and aerodynamic mistuning

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Fig. 7

Variation of magnitude and phase angle of pressure difference coefficient Δcp with interblade phase angle and aerodynamic mistuning

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Fig. 8

Fourier transform magnitudes of surface pressure at IBPA, σ = 135 deg: (a) pressure side, configuration I (b), (b) pressure side, configuration II (b), (c) suction side, configuration I (b), and (d) suction side, configuration II (b)

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Fig. 9

Aerodynamic damping comparison of the baseline case and the one-blade mis-staggering patterns at an oscillation amplitude of α¯=0.5deg and reduced frequency of ω* = 0.244

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Fig. 10

Aerodynamic damping comparison of the baseline case and the alternating blade mis-staggering patterns at an oscillation amplitude of α¯=0.5deg and reduced frequency of ω* = 0.244

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Fig. 11

Aerodynamic damping comparison of the baseline case and the random mis-staggering patterns at an oscillation amplitude of α¯=0.5deg and reduced frequency of ω* = 0.244

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