E3S Web Conf.
Volume 345, 2022XXV Biennial Symposium on Measuring Techniques in Turbomachinery (MTT 2020)
|Number of page(s)||7|
|Published online||29 March 2022|
Blade oscillation mechanism for aerodynamic damping measurements at high reduced frequencies
KTH Royal Institute of Technology, Brinellvägen 68, SE-10044 Stockholm, Sweden
* Corresponding author: email@example.com
Accurate prediction of aerodynamic damping is essential for flutter and forced response analysis of turbomachinery components. Reaching a high level of confidence in numerical simulations requires that the models have been validated against the experiments. Even though a number of test cases have been established over the past decades, there is still a lack of suitable detailed test data that can be used for validation purposes in particular when it comes to aero damping at high reduced frequencies which is more relevant in the context of forced response analysis. A new transonic cascade test rig, currently undergoing commissioning at KTH, has been designed with the goal to provide detailed blade surface unsteady pressure data for compressor blades profiles oscillating at high reduced frequencies. The paper provides an overview of the blade actuation system employed in the test rig and presents the result of a series of bench tests characterizing the blade vibration amplitudes achieved with this actuation system.
© The Authors, published by EDP Sciences, 2022
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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