Influences of cavity leakage on the design of low flow coefficient centrifugal impeller

Wang, Zhiheng; Xi, Guang

doi:10.1007/s11431-010-4238-3

Cited by 7 publications

(2 citation statements)

References 12 publications

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“…7 Barton et al 8 have verified by means of computational fluid dynamic techniques that the surge margin of a centrifugal compressor with an inducer vaned shroud can be improved, while maintaining acceptable high-speed performance. Many others authors have analysed the effect of the cavity's flow on a compressor performance, such as Wang and Xi, 9 who have reported a reduction in the impeller efficiency due to the cavity leakage, which varies with the impeller blade shape as a result of a strong and complex interaction between the main and the leakage flows. Also, Tuo et al 10 have reported experimental results indicating that the unsteady excitation frequency due to interactions between the CT slots and the rotor blades is one of the most important factors influencing compressor performance.…”

Section: Introductionmentioning

confidence: 99%

Analyses of radial compressor stability improvement by casing treatment

Khalfallah¹,

Ghenaiet²

2012

Proceedings of the Institution of Mechanical Engineers, Part A:

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Centrifugal compressors used for turbochargers are required to achieve high performance within wide flow ranges. However, their operability is limited at low mass flow rates by the flow instabilities leading to rotating stall and surge, which could be delayed by a suitable casing treatment. This article presents a numerical investigation aimed at studying the effects of a type of casing treatment on the flow structure through a radial compressor and the subsequent improvement of aerodynamic stability. The considered casing treatment consists of an oblique slot recess inserted in the shroud near the impeller throat and a large annular cavity connecting this slot to the bell-mouth. The flow computations were carried out by means of the code ANSYS-CFX, considering the shear stress transport (k–ω) turbulence model, in order to investigate the effects of the cavity dimensions on improving the stability limit of the compressor. The analysis of flow structure near the stall limit has revealed that the large vortex appearing near the blade tip is being controlled by such a type of casing treatment; hence the stall onset is delayed. As consequence, the operating range and the stall margin are improved by reducing the aerodynamic blockage.

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Section: Introductionmentioning

confidence: 99%

Analyses of radial compressor stability improvement by casing treatment

Khalfallah¹,

Ghenaiet²

2012

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…However, in recent years, studies have focused on investigating the actual structure. Previous studies investigated the influence of the centrifugal compressor cavity on its aerodynamic performance (Wang & Xi, 2011;Wang, Xu, & Xi, 2010). The results of these studies indicate that the influence of leakage is significant in the centrifugal impeller at a flow coefficient below 0.02.…”

Section: Introductionmentioning

confidence: 99%

Influence of rotor–stator component partition structure on the aerodynamic performance of centrifugal compressors

Shi³

et al. 2019

Engineering Applications of Computational Fluid Mechanics

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The partition structure (PS) between the impeller and stationary blade of a centrifugal compressor considerably influences a compressor's performance. Based on computational fluid dynamics, this study constructed a coupling calculation model for the main flow, wheel cover, wheel disk side partition clearance, and sealing structure. Furthermore, we examined the influence that different PS shapes (i.e. circular arc, trapezoidal, and rectangular) and radial clearances (2, 4, and 6 mm) at the entrance of the cavity between the rotor and stator components have on the aerodynamic performance and loss mechanism of the centrifugal compressor using a numerical method. The influence that the PS has on the transition zone between the impeller outlet and stator inlet sections was analysed in detail. According to the results, when the PS was in a circular arc form, with a clearance of 2 mm, it achieved the highest efficiency, which increased the efficiency of the original model by 0.99% and the total pressure ratio by 1.23%. Moreover, an examination of the main flow interaction provided an enhanced insight into the microflow phenomenon in centrifugal compressors. ARTICLE HISTORY

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Aerodynamic effects of impeller-diffuser axial misalignment in low-flow-coefficient centrifugal compressor

Wang

Liu

2014

Sci. China Technol. Sci.

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Influences of cavity leakage on the design of low flow coefficient centrifugal impeller

Cited by 7 publications

References 12 publications

Analyses of radial compressor stability improvement by casing treatment

Analyses of radial compressor stability improvement by casing treatment

Influence of rotor–stator component partition structure on the aerodynamic performance of centrifugal compressors

Aerodynamic effects of impeller-diffuser axial misalignment in low-flow-coefficient centrifugal compressor

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