Theoretical and experimental investigation of design parameter effects on the slip phenomenon and performance of a centrifugal compressor

Rajabpour, Shahram; Manzari, Mehrdaad; Hajilouy-Benisi, Ali

doi:10.24200/sci.2020.53042.3040

Cited by 1 publication

(2 citation statements)

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“…The surge point can be obtained using pressure spectrum (analyzing the pressure downstream of the compressor), the frequency peak which describes the surge was between 18 and 22 Hz [17]. Where  is flow coefficient = Q/2πb2r2U2,  is the pressure coefficient =2∆P/ρU2 2 .…”

Section: Experimental Workmentioning

confidence: 99%

“…Also, the centrifugal compressors have advantages over axial compressors, such as higher pressure ratio, lower weight, and ease of assembly. Therefore, the demand from companies that manufacture cars is increasing, which challenges manufacturers to improve the compression ratio, efficiency and increase the stable operating range [1][2][3]. Improving the specifications of the turbocharger compressor requires an increase in the compression ratio while maintaining the operating range of the panel, thus increasing the engine power production, reducing noise and air pollutants, and thus reducing the overall size of the machine, and increasing its efficiency [4].…”

Section: Introduction and Literature Reviewmentioning

confidence: 99%

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Influence of the Volute Design Parameters on the Flow Phenomena and Performance of the Centrifugal Compressor

Hassan¹,

Hadidi²,

Tharwan³

2022

Preprint

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Influence of the volute design parameters on the stable operating range and the performance of a centrifugal compressor was investigated experimentally for the following design conditions. The volute casing surface roughness was changed from 0 to 200 µm in five steps and tested. The axial distance between the casing and the diffuser cascades (clearance) was varied in five steps as C/b2 = 1.2, 2.4%, 3.6%, 4.8%, and 6% relative to the impeller exit width. The radial distance from the impeller blade exit to the diffuser vane inlet in (vaneless space radius) in six steps as C/r2 = 1.03, 1.05, 1.07, 1.09, 1.11, and 1. 13 relatives to the rotor outlet radius. The volute outlet geometry of a symmetric and tangent with different area ratios from 0.4 to 0.9. Finally, the compressor has been tested experimentally with different pinched vaned diffuser distances relative to the impeller exit width of bp/b2 =1, 0.98, 0.96, 0.94, 0.92, and 0.9. These testes were carried at different compressor operating conditions, and the time variations of the static pressure were recorded using five high-frequency response pressure transducers. A hot-wire anemometer is used to measure the compressor flow rate. The rotating stall and surge at the vaneless zone after the impeller exit can be detected by analyzing the fluctuations of pressure signals and the power spectrum density by using the Fast Fourier Transformation analysis. The experimental results indicated that the compressor with volute casing surface roughness of 100mm gives about 10.9% enhancements in the stable operating and 1% in pressure rise coefficient. The best axial distance between the diffuser vanes and the casing is 2.4% of the impeller blade height and the compressor in this design gives about 12.4% improvements in the stable working range. The compressor with radial vaneless distance of 1.056 gives improvements of about 16.6% in the surge margin, 2% in the pressure recovery and 4% in pressure rise coefficients. The compressor with a pinched diffuser of b/bp of 0.98 gives an improvement of 20.8% in surge point.

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Section: Experimental Workmentioning

confidence: 99%

Section: Introduction and Literature Reviewmentioning

confidence: 99%