A reduced order approach for the vibration of mistuned bladed disk assemblies

Journal Article · Wed Jan 01 04:00:00 EST 1997 · Journal of Engineering for Gas Turbines and Power

DOI:https://doi.org/10.1115/1.2815542· OSTI ID:483761

Yang, M T; Griffin, J H ^[1]

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1. Carnegie Mellon Univ., Pittsburgh, PA (United States). Dept. of Mechanical Engineering

A reduced order approach is introduced in this paper that can be used to predict the steady-state response of mistuned bladed disks. This approach takes results directly from a finite element analysis of a tuned system and, based on the assumption of rigid blade base motion, constructs a computationally efficient mistuned model with a reduced number of degrees of freedom. Based on a comparison of results predicted by different approaches, it is concluded that: the reduced order model displays structural fidelity comparable to that of a finite element model of the entire bladed disk system with significantly improved computational efficiency; and under certain circumstances both the finite element model and the reduced order model predict quite different response from simple spring-mass models.

• Sponsoring Organization: National Aeronautics and Space Administration, Washington, DC (United States)
• OSTI ID: 483761
• Report Number(s): CONF-950629--
• Journal Information: Journal of Engineering for Gas Turbines and Power, Journal Name: Journal of Engineering for Gas Turbines and Power Journal Issue: 1 Vol. 119; ISSN JETPEZ; ISSN 0742-4795
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPUTER CALCULATIONS
MECHANICAL VIBRATIONS
RESPONSE FUNCTIONS
ROTORS
TURBINE BLADES
TURBOMACHINERY