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Towards a comprehensive direct prediction strategy of the effects of mistuning on the forced response of turbomachinery blades

Towards a comprehensive direct prediction strategy of the effects of mistuning on the forced... The objective of the present article is to provide a progress report on, and highlight, some ongoing efforts regarding the available techniques for the direct (i.e. not based on Monte Carlo simulations) prediction of the distribution of the forced response of turbomachinery bladed disks that exhibit small blade‐to‐blade variations in their structural properties (random mistuning). The focus of this effort is on the statistical distributions of the amplitudes of response of a typical blade at a given frequency (level 1), of the maximum responding blade on the disk at a given frequency (level 2), and finally of the maximum responding blade on the disk over a frequency sweep (level 3). When appropriate, emphasis will be placed on the reliability of these techniques as a function of the blade‐to‐blade coupling strength. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Towards a comprehensive direct prediction strategy of the effects of mistuning on the forced response of turbomachinery blades

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References (18)

Publisher
Emerald Publishing
Copyright
Copyright © 1999 MCB UP Ltd. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022669910296909
Publisher site
See Article on Publisher Site

Abstract

The objective of the present article is to provide a progress report on, and highlight, some ongoing efforts regarding the available techniques for the direct (i.e. not based on Monte Carlo simulations) prediction of the distribution of the forced response of turbomachinery bladed disks that exhibit small blade‐to‐blade variations in their structural properties (random mistuning). The focus of this effort is on the statistical distributions of the amplitudes of response of a typical blade at a given frequency (level 1), of the maximum responding blade on the disk at a given frequency (level 2), and finally of the maximum responding blade on the disk over a frequency sweep (level 3). When appropriate, emphasis will be placed on the reliability of these techniques as a function of the blade‐to‐blade coupling strength.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Oct 1, 1999

Keywords: Blades; Prediction; Localization; Turbines

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