High-fidelity calculation of modal damping caused by friction at blade roots for single blades and tuned bladed disc assemblies
Author:
Affiliation:
1. Nanjing University of Aeronautics and Astronautics, Aero-engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, Nanjing, China
2. University of Sussex, Brighton, UK
Abstract
Publisher
SAGE Publications
Subject
Mechanical Engineering
Link
http://journals.sagepub.com/doi/pdf/10.1177/0954406220935144
Reference15 articles.
1. The effect of underplatform dampers on the forced response of bladed disks by a coupled static/dynamic harmonic balance method
2. Theoretical and experimental studies of structural integrity of dovetail joints in aeroengine discs
3. Three-dimensional nonlinear finite element analysis of dovetail joints in aeroengine discs
4. Effects of Damping and Varying Contact Area at Blade-Disk Joints in Forced Response Analysis of Bladed Disk Assemblies
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