On Forced Response of a Rotating Integrally Bladed Disk: Predictions and Experiments

Gibert, Claude; Kharyton, Vsevolod; Thouverez, Fabrice; Jean, Pierrick

doi:10.1115/gt2010-23610

Cited by 12 publications

(5 citation statements)

References 13 publications

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“…For each frequency, the 2D DFT yielded the spatial decomposition arranged in nodal diameters. The full spectrum analysis allows identifying the direction of the rotating wave for each nodal diameter [16]. A negative nodal diameter was interpreted as a backward traveling wave.…”

Section: Quasi-staticmentioning

confidence: 99%

Experimental Analysis of Dynamic Interaction Between a Centrifugal Compressor and its Casing

Almeida

Gibert

Thouverez

et al. 2014

Volume 7B: Structures and Dynamics

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In turbomachinery, one way to improve aerodynamic performance and reduce fuel consumption consists of minimizing the clearance between rotor and casing. Yet the probability of contact is increased and this may lead in some specific conditions to a large and even unstable excitation on the impeller and stator. To achieve better understanding of the dynamic behavior occurring during the blade-to-casing contact, many numerical studies have been conducted but only a few experiments have been reported in the literature thus far. The interaction experiment reported in this paper involves a low-pressure, rotating centrifugal compressor and its casing tested in a vacuum chamber. Contact is initiated by introducing a gap near zero, and certain events with significant dynamic levels are observed during the run-up. Measurements are performed using strain gauges on both the rotating and stationary parts and a Scanning Laser Doppler Vibrometer on the stator. This research focuses on an analysis of the recorded data. Time series data are also analyzed by means of standard signal processing and a full spectrum analysis in order to identify the direction of traveling wave propagation on the two structures as well as nodal diameters and frequencies. The dynamic response of structures is accompanied by variations in other physical parameters such as temperature, static deformed shapes, speed and torque. A wearing pattern is evaluated following the contact experiments. The spectral content of response is dominated by frequency modes excited by engine orders as well as by sidebands due to inherent system non-linearity.

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Section: Quasi-staticmentioning

confidence: 99%

Experimental Analysis of Dynamic Interaction Between a Centrifugal Compressor and its Casing

Almeida

Gibert

Thouverez

et al. 2014

Volume 7B: Structures and Dynamics

View full text Add to dashboard Cite

show abstract

“…Holland et al 15 proposed an integrated testing and calibration procedure to identify the mistuning and simulate traveling wave excitation for blisk. Gibert et al 16 described an experimental setup to measure the dynamic response of blisk under traveling wave excitation and the excitation force was provided by piezoelectric actuators and phase-shifting circuit. The methods mentioned in the above studies can achieve the simulation of traveling wave excitation basically.…”

Section: Introductionmentioning

confidence: 99%

Nodal diameter vibration identification of coated blisk under traveling wave excitation

Jin

Sun

2020

Journal of Low Frequency Noise, Vibration and Active Control

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It is seen that blisk will be in a nodal diameter vibration state under the engine order excitation, which can be simulated by traveling wave excitation. The nodal diameters rotate on the blisk and it is necessary to identify the specific form of the nodal diameter vibration. Here, based on the determination of nodal diameter vibration parameters, a novel identification method of the nodal diameter vibration was proposed through the experimental test. Specifically, a traveling wave excitation system was built using the LabVIEW control software and noncontact magnetic exciters. Based on the description of resonant state of blisk, the identification principle formulas of the nodal diameter vibration were derived and the identification procedure was given. Taking uncoated and coated blisks as the research objects, the identification method was demonstrated. The identification results showed that the shape, direction, speed, and period of nodal diameter vibration were successfully obtained by the proposed method. In addition, it was found that coatings have a damping effect on blisk. Because of the coating introduction, the blisk vibration response was reduced, the rotation speed of nodal diameter was slowed down, and the rotation period of nodal diameter was increased.

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“…[13][14][15][16] Regarding the bladed disk of aero-engine, the blade becomes thinner and thinner, and the geometry is more complicated. 17 Therefore, Huang and Kuang 18 used Galerkin method to carry out research the mode localization of a bladed disk considering the Coriolis effect. Their results implied that the mode localization of bladed disk with the consideration of the Coriolis effect was related to the rotational speed.…”

Section: Introductionmentioning

confidence: 99%

Vibration localization for a rotating mistuning bladed disk with the Coriolis effect by a state-space decoupling method

Kan

Zhou

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Slight deviations of blades due to manufacturing tolerances can cause mistuning of bladed disk leading to localized vibration, which can accelerate fatigue. Moreover, the rotating blades are subjected to the Coriolis effect and the influence of the Coriolis force on the natural frequencies of high-speed rotational bladed disks such as those of an aero-engine become more apparent. In this paper, the effect of Coriolis force on the forced response localization of a mistuned bladed disk are investigated, for conditions where the natural frequency located in the first and second modal families of the bladed disk. Mistuning is introduced by varying the Young’s modulus of each blade. Due to the asymmetric Coriolis matrix, it is not possible to directly decouple the system. A state-space decoupling method is developed to decouple the system to effectively calculate the forced response of bladed disk with the consideration of the Coriolis effect. The results show that response localization factor is increased by 13.09% considering the Coriolis force compared to the system without considering the Coriolis effect, in the case of where the first modal family is considered. In addition, the response localization factor with the consideration of the Coriolis force is decreased by 30.85% compared to the system without considering the Coriolis force, when the second modal family is considered. It indicates that the forced response localization with the consideration of the Coriolis effect will be changed obviously with the rotational speed increasing, when the concerning natural frequency is located in the first and second modal families. Furthermore, the effect of Coriolis force causes changes in the resonant frequencies and resonant amplitude, but does not introduce additional resonant peaks for the case of the mistuned bladed disk.

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On Forced Response of a Rotating Integrally Bladed Disk: Predictions and Experiments

Cited by 12 publications

References 13 publications

Experimental Analysis of Dynamic Interaction Between a Centrifugal Compressor and its Casing

Experimental Analysis of Dynamic Interaction Between a Centrifugal Compressor and its Casing

Nodal diameter vibration identification of coated blisk under traveling wave excitation

Vibration localization for a rotating mistuning bladed disk with the Coriolis effect by a state-space decoupling method

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