Next-Generation Modeling, Analysis, and Testing of the Vibration of Mistuned Bladed Disks PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 27
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Book Description
Turbomachinery rotors, or bladed disks, are known to suffer from severe vibration problems due to small, random deviations (mistuning) of the blade properties. Mistuning can lead to dramatic increases in the maximum blade stress and cause high cycle fatigue (HCF), which is a major cost, readiness, and safety concern for the U.S. Air Force. The primary objective of this research was to provide significantly improved understanding, modeling, and prediction of the vibration response of mis-tuned bladed disk systems by including the effects of important phenomena that had been largely neglected in previous mistuning models. The models developed in this research program were used to investigate the interaction of blade mistuning with aerodynamic coupling, stage-to-stage connections for multistage rotors, blade damage, and nonlinearities. In addition, key mistuning phenomena were examined through vibration testing of blisks (single-piece bladed disks). New methods were developed for identifying blade mistuning parameters from test data and for running experimental Monte Carlo assessments of the effects of mistuning on the system forced response.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 27
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Book Description
Turbomachinery rotors, or bladed disks, are known to suffer from severe vibration problems due to small, random deviations (mistuning) of the blade properties. Mistuning can lead to dramatic increases in the maximum blade stress and cause high cycle fatigue (HCF), which is a major cost, readiness, and safety concern for the U.S. Air Force. The primary objective of this research was to provide significantly improved understanding, modeling, and prediction of the vibration response of mis-tuned bladed disk systems by including the effects of important phenomena that had been largely neglected in previous mistuning models. The models developed in this research program were used to investigate the interaction of blade mistuning with aerodynamic coupling, stage-to-stage connections for multistage rotors, blade damage, and nonlinearities. In addition, key mistuning phenomena were examined through vibration testing of blisks (single-piece bladed disks). New methods were developed for identifying blade mistuning parameters from test data and for running experimental Monte Carlo assessments of the effects of mistuning on the system forced response.
Author: Jia Li
Publisher:
ISBN:
Category :
Languages : en
Pages : 398
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Author: Sang-Ho Lim
Publisher:
ISBN:
Category :
Languages : en
Pages : 482
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Author: Bereket Kiflu
Publisher:
ISBN:
Category : Disks, Rotating
Languages : en
Pages : 138
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Author: Ming-Ta Yang
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ISBN:
Category :
Languages : en
Pages : 0
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Author: Jan Ronnie Bladh
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ISBN:
Category :
Languages : en
Pages : 596
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Author: Ronnie Bladh
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, Jun 2-5, 1998.
Author: Anthony Picou
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The intentional mistuning, also called detuning has been identified as an efficient technological way for reducing the sensitivity of the forced response of bladed disks to unintentional mistuning (simply called mistuning), caused by the manufacturing tolerances and the small variations in the mechanical properties from blade to blade. The intentional mistuning consists in detuning the bladed disk structure by using partial or alternating patterns of different sector types. However, the recent technological improvements that include the use of more flexible and lighter blades can lead to large strains/displacements, which requires the use of nonlinear dynamic equations involving geometric nonlinearities. This work is devoted to the robust analysis of the effects of geometric nonlinearities on the nonlinear dynamic behavior of rotating detuned bladed disks in presence of mistuning. The detuning corresponds to uncertainties in the computational model, and are taken into account by a probabilistic approach. This thesis presents a series of novel results in dynamics of rotating bladed disks with mistuning and detuning in presence of nonlinear geometrical effects. The structural responses are computed in the time domain and are analyzed in the frequency domain. The frequency analysis exhibits responses outside the frequency band of excitation. The confidence region of the stochastic responses allows the robustness to be analyzed with respect to uncertainties, that is to say with respect to the level of mistuning. The bladed disk structure, which is used for the numerical simulations, is made up of 24 blades for which several different detuned patterns are investigated with and without mistuning.
Author: Giulia Massazza
Publisher:
ISBN:
Category :
Languages : en
Pages : 208
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Author: Gangbing Song
Publisher: MDPI
ISBN: 3038427853
Category : Technology & Engineering
Languages : en
Pages : 263
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Book Description
This book is a printed edition of the Special Issue "Energy Dissipation and Vibration Control: Modeling, Algorithm and Devices" that was published in Applied Sciences
