Effects of natural frequencies on the failure of R1 compressor blades

Poursaeidi, Esmaeil; Babaei, Alireza; Arhani, M. R. Mohammadi; Arablu, Masoud

doi:10.1016/j.engfailanal.2012.05.013

Cited by 57 publications

(22 citation statements)

References 4 publications

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“…Xu et al [15] researched stress and vibration of blades of a large axial flow fan by experiments and numerical simulation, finding that unsteady pressure fluctuation had very large effects on fan vibration characteristics. Poursaeidi et al [16,17] used ANSYS to research blade failure characteristics of a first-stage rotor of a gas compressor, finding that resonance under first-order and second-order natural frequencies was the major reason for blade fatigue cracking.…”

Section: Introductionmentioning

confidence: 99%

Axial Spacing Effects on Rotor-Rotor Interaction Noise and Vibration in a Contra-Rotating Fan

Luan

Weng

Liu

et al. 2019

International Journal of Aerospace Engineering

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Because of the potential technical advantages, the contra-rotation technology has become a renewed interest in aviation and other applications. Contra-rotation increases efficiency in comparison with the single-rotor design, but this advantage is not fully harnessed. The axial spacing of two-stage contra-rotating blade rows has a significant impact on a contra-rotating fan/compressor. The results show that with a contra-rotation pattern, the strong unsteadiness of two-stage rotors is caused by the rotor-rotor interaction. The unsteadiness of rotor 1 is caused by the potential disturbance, and the upstream wake leads to the strong unsteadiness of rotor 2. With the increase of axial spacing, the rotor-rotor interaction is weakened, while unsteady features of two-stage rotor blades tend to be consistent. The acoustic and vibration effects of axial spacing are studied. It is found that the axial spacing has great influence of aerodynamic noise. The mean value of sound pressure level decreases by 17.2 dB in total when the axial spacing increased to 1.1 chord from 0.3 chord. For the accuracy of calculation, the scattering effect of the casing wall should be considered in the prediction of the noise. The axial spacing does not have obvious effects on the natural frequencies of the two-stage rotor blades but has certain effect on blade deformation.

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Section: Introductionmentioning

confidence: 99%

Axial Spacing Effects on Rotor-Rotor Interaction Noise and Vibration in a Contra-Rotating Fan

Luan

Weng

Liu

et al. 2019

International Journal of Aerospace Engineering

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“…These authors in another research (Kim & Lee, 2013), have been studied modal characteristics according to the tip shape and assembly condition of the turbine blade. Effects of natural frequencies on the failure of R1 compressor blades have been discussed by Poursaeidi et al (2012). They concluded that the resonance of the blades under the first and second natural frequency modes is the primary cause of the fatigue fractures of these blades.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical modal analysis of the first and second stage compressor blades

Ghoreishi¹,

Salari²,

Pourhosseini³

et al. 2019

10.5267/j.esm

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In this paper, the first and second stage compressor blades of a gas turbine were studied by the experimental and numerical modal analyses. At first, the geometric models of these blades were generated by the 3D scanner and then the mode shapes and the natural frequencies of each blade were extracted by a series of numerical modal analyses. The numerical results were compared with the data obtained from the experimental modal analysis and the validity and accuracy of the developed numerical models were confirmed. Unlike most studies that use fixed-free boundary condition for performing a modal analysis, this objective was pursued by applying a free-free boundary condition. This study also investigated the effect of using wax or glue for mounting the accelerometer on the blade by assessing the FRF curves obtained from the modal tests in the frequency range of 0-10000 Hz. The sensitivity of the test results to applying free-free boundary condition, the number of accelerometers and their positions were investigated by defining three modal test configurations. The results obtained by these test configurations were compared with the results of numerical analyses and finally, the best configuration for the modal test of the studied compressor blade was determined.

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“…In recent years and due to financial and irrecoverable life damages, prevention of failure in rotating machines is vitally important. Many researches, by introducing the phenomenon of high cycle fatigue as the main cause of failure, have been determined blade as a critical component of machines [1][2][3][4][5][6]. Among researches performed by studying blade vibration under different condition [7][8][9][10], which have been provided diverse methods to reduce blade vibrations [11][12][13][14], centrifugal pendulum vibration absorber is a proper way to suppress blade vibration especially in resonance condition [15,16].…”

Section: Introductionmentioning

confidence: 99%

“…(5) https://www.cambridge.org/core/terms. https://doi.org/10.1017/jmech.2016.20Downloaded from https://www.cambridge.org/core.…”

mentioning

confidence: 99%

Optimum Design of Damped Vibration Absorber for Rotationally Periodic Structures

2016

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In this study, a damped centrifugally driven order-tuned vibration absorber designed for vibration reduction in rotating flexible structures, bladed disk assemblies and blisk such as turbine blades, compressor and fan blades, pump and helicopter rotor blades etc. during steady operation with constant speed and under engine order excitation (e.o excitation). Effect of mistuning is disregarded. System is assumed with fully cyclic symmetry. The disk is imposed as being rigid. Elastic behavior for blades is supposed. A model with two degree of freedom is extracted for the blades. Each blade is fitted with nominally identical damped order-tuned vibration absorber that is moved in a circular path. Aerodynamic damping and coupling effects between the blades are considered. Optimal values of parameters of the absorber, to suppress blade vibration especially in resonance condition, are derived by Genetic Algorithm (GA) and MATLAB software. H2 optimization criterion is used. It is observed that with the deviation of each parameter from the optimal condition, the system response is moved away from the ideal design situation and all of the absorbers’ design parameters have definite effects on the system frequency response and on the dissipated energy during vibration. Therefore, ignorance of the effect of one of those parameters (which was happened in literature) affected the system response completely. Literature is reviewed and validity of the results is confirmed.

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Effects of natural frequencies on the failure of R1 compressor blades

Cited by 57 publications

References 4 publications

Axial Spacing Effects on Rotor-Rotor Interaction Noise and Vibration in a Contra-Rotating Fan

Axial Spacing Effects on Rotor-Rotor Interaction Noise and Vibration in a Contra-Rotating Fan

Experimental and numerical modal analysis of the first and second stage compressor blades

Optimum Design of Damped Vibration Absorber for Rotationally Periodic Structures

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