Roles of recirculating bubble on the performance of centrifugal compressors

Lin, Yun; Fan, Tengbo; Zheng, Xinqian

doi:10.1016/j.ast.2021.107073

Cited by 7 publications

(3 citation statements)

References 20 publications

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“…In Figure 11(a), strong shock waves stand on the blade suction surface near the leading edge (will be shown in Figure 12) and prevent low-energy fluid from flowing back to the inducer inlet duct and forming the recirculating bubble reported in reference. 25 So, there is not any reverse flow around the inducer tips. In contrast, the reverse flow develops upstream along the meridional direction on the shroud casing in Figure 11(b) and (c).…”

Section: Results and Analysismentioning

confidence: 99%

DES analysis on effects of variable geometry inlet orifice on a centrifugal compressor

Liu

Zhao

Song

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part D:

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A variable geometry inlet configuration can improve the off-design aerodynamic performance of a turbocharger compressor by actively modulating the internal flow field. As the core part of the configuration, the variable geometry orifice is arranged in front of the compressor inducer. Its novelty is to actively regulate the compressor inlet flow area at an off-design point without causing significant impact at the design point. In this paper, the effects of the orifice on compressor performance and internal flow field are investigated using experiments and numerical simulations. The experimental and the numerical results confirm the variable inlet configuration to be a promising method for extending the compressor operation range. The DES calculations reveal incidence angle reduction at inducer inlet, shock wave migration to a lower radius from blade tip, formation of the aft-loaded impeller, reduced difference between jet and wake flows at impeller exit, and turbulent flow enhancement in the diffuser. Based on understanding the orifice’s effects on the centrifugal compressor, a design suggestion is proposed for the variable geometry compressor of this sort.

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Section: Results and Analysismentioning

confidence: 99%

DES analysis on effects of variable geometry inlet orifice on a centrifugal compressor

Liu

Zhao

Song

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part D:

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“…This indicates that the variation of inlet distortion pattern changes the spatial characteristic of stall inception. When a centrifugal compressor approaches the stall margin, a recirculating bubble 34 initialized at the impeller inlet due to the reversed flow, which is caused by the adverse pressure gradient in the streamwise direction. The reversed flow, which has been worked by the impeller, has a high circumferential velocity and can be identified by the entropy increase of mixing loss.…”

Section: Stall Inceptionmentioning

confidence: 99%

Effect of bend-induced inlet distortion on a centrifugal compressor performance and stall inception

Wang

Zhao

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Bend pipes are usually installed upstream of a centrifugal compressor because of spatial constraints. With the interaction between radial pressure gradient and centrifugal force in bend pipe, a pair of counter-rotating vortices (Dean vortices) is formed after the fluids passed through the bend, and the shape of Dean vortices keeps changing in the straight pipe between the bend and compressor. The effects of the changed Dean vortices on the aerodynamic performance and stall inception of a centrifugal compressor are investigated with an experimentally validated numerical method based on four models, in which the distance of the straight pipe located between the bend and the compressor varies from 0D to 1D through 1/4D and 1/2D. The results show that as the straight pipe length increases from 0D to 1D, both the total pressure deficit at compressor inlet and the flow separations at inlet pipe symmetry plane are enlarged, and the mass flow rate distribution of full-annulus become more fluctuant. As a consequence, the compressor aerodynamic performance degrades and its maximum flow capacity decreases. More importantly, bend-induced inlet distortion has the effect of inducing/suppressing impeller stall inception, it depends on the location and intensity of swirl distortion and total pressure distortion. The low total pressure region located at impeller tip leads to reversed flow and stall inception, while the positive pre-swirl component in swirl distortion decreases the incidence and suppresses stall inception. These results provide a reference for the design of upstream inlet curved pipes of centrifugal compressors.

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“…It forms near the leading edge of the impeller blade, at the inlet to the compressor. It has a form of a recirculating zone of fluid, which might be local or occur around a whole annulus of the compressor and change its size with varying mass flow [42]. Inlet recirculation is responsible for increased loss in the compression system [6] and can be regarded as an early symptom of approaching surge [29].…”

Section: Inlet Recirculationmentioning

confidence: 99%

Comparison of Empirical Mode Decomposition and Singular Spectrum Analysis for Quick and Robust Detection of Aerodynamic Instabilities in Centrifugal Compressors

Stajuda

Cava

Liśkiewicz

2022

Sensors

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Aerodynamic instabilities in centrifugal compressors are dangerous phenomena affecting machine efficiency and in severe cases leading to failure of the compressing system. Quick and robust instability detection during compressor operation is a challenge of utmost importance from an economical and safety point of view. Rapid indication of instabilities can be obtained using a pressure signal from the compressor. Detection of aerodynamic instabilities using pressure signal results in specific challenges, as the signal is often highly contaminated with noise, which can influence the performance of detection methods. The aim of this study is to investigate and compare the performance of two non-linear signal processing methods—Empirical Mode Decomposition (EMD) and Singular Spectrum Analysis (SSA)—for aerodynamic instability detection. Two instabilities of different character, local—inlet recirculation and global—surge, are considered. The comparison focuses on the robustness, sensitivity and pace of detection—crucial parameters for a successful detection method. It is shown that both EMD and SSA perform similarly for the analysed machine, despite different underlying principles of the methods. Both EMD and SSA have great potential for instabilities detection, but tuning of their parameters is important for robust detection.

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Roles of recirculating bubble on the performance of centrifugal compressors

Cited by 7 publications

References 20 publications

DES analysis on effects of variable geometry inlet orifice on a centrifugal compressor

DES analysis on effects of variable geometry inlet orifice on a centrifugal compressor

Effect of bend-induced inlet distortion on a centrifugal compressor performance and stall inception

Comparison of Empirical Mode Decomposition and Singular Spectrum Analysis for Quick and Robust Detection of Aerodynamic Instabilities in Centrifugal Compressors

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