Minimizing Blade Dynamic Response in a Bladed Disk Through Design Optimization
Author:
Affiliation:
1. Defence Science and Technology Organization, Fishermen’s Bend, Victoria 3207, Australia
2. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.11526
Reference33 articles.
1. Effect of Mistuning on the Vibration of Turbo-Machine Blades Induced by Wakes
2. The effects of detuning upon the forced vibrations of bladed disks
3. Vibration Amplitudes of Compressor Blades Resulting From Scatter in Blade Natural Frequencies
4. Research Note: Effect of Mistuning on Forced Vibration of Blades with Mechanical Coupling
5. Model Development and Statistical Investigation of Turbine Blade Mistuning
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