Compact, Generalized Component Mode Mistuning Representation for Modeling Bladed Disk Vibration
Author:
Affiliation:
1. University of Michigan, Ann Arbor, Michigan 48109-2125
2. McGill University, Montreal, Quebec H3A 2K6, Canada
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.13172
Reference32 articles.
1. Flutter and Resonant Vibration Characteristics of Engine Blades
2. Forced Response of Bladed Disk Assemblies--A Survey
3. Modeling and Analysis of Mistuned Bladed Disk Vibration: Current Status and Emerging Directions
4. Coupling of Turbomachine Blade Vibrations Through the Rotor
5. Vibration Amplitudes of Compressor Blades Resulting From Scatter in Blade Natural Frequencies
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