Investigation of an Axial Fan-Blade Stress and Vibration Due to Aerodynamic Pressure Field and Centrifugal Effects

Xu, C.; Amano, Ryoichi S.; Lee, Eng Kwong

doi:10.1299/jsmeb.47.75

Cited by 12 publications

(9 citation statements)

References 9 publications

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“…Palazotto and Shipman [14] assumed a two-dimensional turbine blade as a slab model, computed dynamic stress distribution and vibration amplitude of the turbine blade, and explored high-cycle fatigue courses of the blade. 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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“…The gas then is directed to a radial annular vaned or vaneless diffuser and finally moves into a volute or collector to deliver the compressed gas to the next stage or send it to the next components [1][2][3][4][5][6][7]. Unlike an axial compressor or fan [8], the work input for a centrifugal compressor is almost independent of the nature of the flow. A centrifugal compressor can be designed with much higher De Haller number than an axial compressor can achieve.…”

Section: Introductionmentioning

confidence: 99%

Meridional Considerations of the Centrifugal Compressor Development

Amano

2012

International Journal of Rotating Machinery

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Centrifugal compressor developments are interested in using optimization procedures that enable compressor high efficiency and wide operating ranges. Recently, high pressure ratio and efficiency of the centrifugal compressors require impeller design to pay attention to both the blade angle distribution and the meridional profile. The geometry of the blades and the meridional profile are very important contributions of compressor performance and structure reliability. This paper presents some recent studies of meridional impacts of the compressor. Studies indicated that the meridional profiles of the impeller impact the overall compressor efficiency and pressure ratio at the same rotational speed. Proper meridional profiles can improve the compressor efficiency and increase the overall pressure ratio at the same blade back curvature.

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“…The flow exit from diffuser needs a volute or collector to deliver the flow to the next stage or send to the next components [1][2][3][4][5]. Unlike an axial compressor or fan [6], the work input for centrifugal compressor is almost independent of the nature of the flow. A centrifugal compressor can be designed with much higher De Haller number than an axial compressor can achieve.…”

Section: Introductionmentioning

confidence: 99%

Study of the Flow in Centrifugal Compressor

Xu¹,

Amano²

2010

International Journal of Fluid Machinery and Systems

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Reducing the losses of the tip clearance flow is one of the keys in an unshrouded centrifugal compressor design and development because tip clearances are large in relation to the span of the blades and also centrifugal compressors produce a sufficiently large pressure rise in single stage. This problem is more acute for a low flow high-pressure ratio impeller design. The large tip clearance would cause flow separations, and as a result it would drop both the efficiency and surge margin. Thus a design of a high efficiency and wide operation range low flow coefficient centrifugal compressor is a great challenge. This paper describes a recent development of high efficiency and wide surge margin low flow coefficient centrifugal compressor. A viscous turbomachinery optimal design method developed by the authors for axial flow machine was further extended and used in the centrifugal compressor design. The compressor has three main parts: impeller, a low solidity diffuser and volute. The tip clearance is under a special consideration in this design to allow impeller insensitiveness to the clearance. A patented three-dimensional low solidity diffuser design method is used and applied to this design. The compressor test results demonstrated to be successful to extend the low solidity diffusers to high-pressure ratio compressor. The compressor stage performance showed the total to static efficiency of the compressor being about 85% and stability range over 35%. The test results are in good agreement with the design.

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Investigation of an Axial Fan-Blade Stress and Vibration Due to Aerodynamic Pressure Field and Centrifugal Effects

Cited by 12 publications

References 9 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

Meridional Considerations of the Centrifugal Compressor Development

Study of the Flow in Centrifugal Compressor

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