Mistuned Rotor Reduced Order Modeling with Surrogate-Modeled Airfoil Substructures
Author:
Affiliation:
1. Air Force Research Laboratory
2. Universal Technology Corporation
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2017-1600
Reference21 articles.
1. Uncertainty treatment in forced response calculation of mistuned bladed disk
2. Vibratory Parameters of Blades From Coordinate Measurement Machine Data
3. Flutter and Resonant Vibration Characteristics of Engine Blades
4. Impact of Geometric Variability on Axial Compressor Performance
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1. Numerical Methods for Calculating Component Modes for Geometric Mistuning Reduced-Order Models;Journal of Engineering for Gas Turbines and Power;2021-12-07
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3. Accelerated Multifidelity Emulator Modeling for Probabilistic Rotor Response Study;Journal of Engineering for Gas Turbines and Power;2019-11-19
4. Emulation of Frequency and Mode Shape Variation of As-manufactured Airfoils with Eigenvalue Veering and Crossing;AIAA Scitech 2019 Forum;2019-01-06
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