The problem of determining the worst-case mistuning pattern and robust maximum mistuning forced response of a mistuned bladed rotor is formulated and solved as an optimization problem. This approach is exemplified on a two-degrees-of-freedom per blade disk model, two three-degrees-of-freedom per blade disk models, and a mistuned two-stage bladed rotor. The results of the optimum search of the worst-case mistuning patterns for the lumped parameter models are analyzed, which reveals that the maximum blade forced response in a mistuned bladed disk is associated with mistuning jump, which causes strong localization of the vibration response in a particular blade. The mistuning jump-localization phenomenon has been observed for all of the numerical examples, and it is also demonstrated that the highest response was always experienced by a blade of mistuning value jump. The two- and three-degrees-of-freedom per blade disk models are also for determination of its sensitivity coefficients with respect to mistuning variation. Studies show that there is not a threshold of mistuning beyond which the maximum forced response levels off, or even drops, as the degree of mistuning is increased further. The maximum magnification factor is found to increase as the mistuning level is increased and reaches a maximum value at the upper limit of the mistuning level. The influence of the multistage coupling is revealed by comparing the results of single-stage analysis with that of the multistage case. The computed results have been compared with the Monte Carlo simulation produced, and it is demonstrated that the accuracy and efficiency of the maximum amplitude magnification factor computed by the presented method can be better than that of Monte Carlo simulations.
Skip Nav Destination
Article navigation
December 2010
Research Papers
Mistuning Forced Response Characteristics Analysis of Mistuned Bladed Disks
Haitao Liao,
Haitao Liao
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Search for other works by this author on:
Jianjun Wang,
Jianjun Wang
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Search for other works by this author on:
Jianyao Yao,
Jianyao Yao
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Search for other works by this author on:
Qihan Li
Qihan Li
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Search for other works by this author on:
Haitao Liao
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Jianjun Wang
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Jianyao Yao
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, China
Qihan Li
School of Jet Propulsion,
Beijing University of Aeronautics and Astronautics
, Beijing 100191, ChinaJ. Eng. Gas Turbines Power. Dec 2010, 132(12): 122501 (11 pages)
Published Online: August 20, 2010
Article history
Received:
June 25, 2009
Revised:
January 4, 2010
Online:
August 20, 2010
Published:
August 20, 2010
Citation
Liao, H., Wang, J., Yao, J., and Li, Q. (August 20, 2010). "Mistuning Forced Response Characteristics Analysis of Mistuned Bladed Disks." ASME. J. Eng. Gas Turbines Power. December 2010; 132(12): 122501. https://doi.org/10.1115/1.4001054
Download citation file:
Get Email Alerts
Study Of Tandem Rotor Dual Wake Interaction With Downstream Stator Under Unsteady Numerical Approach
J. Eng. Gas Turbines Power
An Efficient Uncertainty Quantification Method Based on Inter-Blade Decoupling for Compressors
J. Eng. Gas Turbines Power (April 2025)
Experimental Design Validation of a Swirl-Stabilized Burner With Fluidically Variable Swirl Number
J. Eng. Gas Turbines Power (April 2025)
Experimental Characterization of a Bladeless Air Compressor
J. Eng. Gas Turbines Power (April 2025)
Related Articles
Friction Damper Optimization: Simulation of Rainbow Tests
J. Eng. Gas Turbines Power (October,2001)
Stability Increase of Aerodynamically Unstable Rotors Using Intentional Mistuning
J. Turbomach (January,2008)
The Influence of a Cracked Blade on Rotor’s Free Vibration
J. Vib. Acoust (October,2008)
A Comprehensive Procedure to Estimate the Probability of Extreme Vibration Levels Due to Mistuning
J. Eng. Gas Turbines Power (November,2010)
Related Proceedings Papers
Related Chapters
Introduction I: Role of Engineering Science
Fundamentals of heat Engines: Reciprocating and Gas Turbine Internal Combustion Engines
Regression Based Neural Network for Studying the Vibration Control of the Rotor Blade for Micro-Unmanned Helicopter
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis