A reduced-order model of mistuning using a subset of nominal system modes

Journal of Engineering for Gas Turbines and Power

Volumn 123, Issue 4, 2001, Pages 893-900

  Yang, M T ^a   Griffin, J H ^a  

^a CARNEGIE MELLON UNIVERSITY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

FINITE ELEMENT METHOD; HARMONIC ANALYSIS; STRESSES; TURBOMACHINE BLADES;

COMPUTATIONAL EFFICIENCY;

DISKS (STRUCTURAL COMPONENTS);

BLADE; GAS TURBINE; MODEL; RESONANCE; VIBRATION;

EID: 0035482548     PISSN: 07424795     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1385197     Document Type: Article

References (13)

1. Effect of mistuning on the vibration of turbomachine blades induced by wakes
2. Resonant vibration levels of a mistuned bladed disk
3. Forced vibrations of a single stage axial compressor rotor
4. Model development and statistical investigation of turbine blade mistuning
5. A higher order technique to compute the statistics of forced response of a mistuned bladed disk assembly
6. Localization phenomena in mistuned assemblies with cyclic symmetry, Part II: Forced vibrations
7. An adaptive perturbation scheme for the analysis of mistuned bladed disks
8. Forced response of mistuned bladed disks using reduced-order modeling
9. A reduced order approach for the vibration of mistuned bladed disk assemblies
10. A normalized modal eigenvalue approach for resolving modal interaction
11. Aeroelastic formulation for tuned and mistuned rotors
12. The role of eigenvectors in aeroelastic analysis
13. A reduced order model of unsteady flows in turbomachinery