Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

He, Xiao; Zheng, Xinqian

doi:10.3390/app7101081

Cited by 12 publications

(8 citation statements)

References 42 publications

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“…The performance of each design point is evaluated by total pressure ratio and total to total isentropic efficiency from compressor inlet to the diffuser outlet. Pressure ratio is calculated by means of following relation: Pr = P 03 dṁ/ṁ /P 00 (9) In which the numerator is mass flow average of total pressure at the diffuser outlet. Using pressure ratio, the isentropic efficiency is calculated using Equation (10).…”

Section: Effective Parameter Identificationmentioning

confidence: 99%

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Optimization of a Centrifugal Compressor Using the Design of Experiment Technique

Mojaddam

Pullen

2019

Applied Sciences

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Centrifugal compressor performance is affected by many parameters, optimization of which can lead to superior designs. Recognizing the most important parameters affecting performance helps to reduce the optimization process cost. Of the compressor components, the impeller plays the most important role in compressor performance, hence the design parameters affecting this component were considered. A turbocharger centrifugal compressor with vaneless diffuser was studied and the parameters investigated included meridional geometry, rotor blade angle distribution and start location of the main blades and splitters. The diffuser shape was captured as part of the meridional geometry. Applying a novel approach to the problem, full factorial analysis was used to investigate the most effective parameters. The Response Surface Method was then implemented to construct the surrogate models and to recognize the best points over a design space created as based on the Box-Behnken methodology. The results highlighted the factors that affected impeller performance the most. Using the Design of Experiment technique, the model which optimized both efficiency and pressure ratio simultaneously delivered a design with 3% and 11% improvement in each respectively in comparison to the initial impeller at the design point. Importantly, this was not at the expense of sacrificing range, of critical concern in compressor design.

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Section: Effective Parameter Identificationmentioning

confidence: 99%

“…Many parameters are considered in this regard. For example optimization techniques were implemented to optimize the blade profile [6], meridional profiles [7,8], blade sweep angle [9], the splitter [10], the vaneless diffuser [11] and there are many others.…”

Section: Introductionmentioning

confidence: 99%

Optimization of a Centrifugal Compressor Using the Design of Experiment Technique

Mojaddam

Pullen

2019

Applied Sciences

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“…In the field of aerodynamic and turbine machinery design, cascade stacking design in 3D [15][16][17] was considered to improve performance. Rosic et al [18] compared three types of static blades with low aspect ratio turbines and found that the positive wrap angle difference affects the load distribution of blades which could suppress the leakage flow on the hub surface.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Impact of Trailing Edge Stacking Styles on Hydraulic Performance in the Multistage Submersible Pump Space Diffuser

Zhang,

Cao,

et al. 2023

Processes

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To investigate the effect of the different wrap angles from the hub to the shroud surface in the space diffuser (i.e., the trailing edge stacking style) on the principle of corner separation vortex flow, a numerical simulation method has been conducted in a multistage submersible pump. Building a linear equation on the profile line of the diffuser trailing edge to optimize the wrap angle on every spanwise from the hub to the shroud, and the mapping response relationship between the wrap angle difference and the hydraulic performance in the space diffuser has been analyzed. Under the variable wrap angle difference (Δϕ=ϕhub−ϕshroud), the secondary flows in different directions, non-uniformity, diffuser efficiency, and pressure recovery are compared. The positive wrap angle difference (i.e., the shroud wrap angle is smaller than the hub one) improves the strength of the secondary flow and partly corner separation vortex in the diffuser, so the hydraulic characteristic of positive cases is better than the negative wrap angle difference. Moreover, in scheme A (in which the hub wrap angle is constant and the shroud wrap angle decreasing), the transversal secondary flow has been weakened, the low-energy fluid located in the corner has been suppressed, the extensional secondary flow has been increased, the diffuser hydraulic performance has been improved, and unidirectionally increases with the wrap angle difference increasing. When the shroud wrap angle is constant, the extensional secondary flow has been enhanced by the increasing hub wrap angle. Meanwhile, the increasing extensional secondary flow has been countered by the deteriorating extensional flow at the diffuser inlet and transversal secondary flow, the diffuser hydraulic performance increases and then decreases as the wrap angle difference increases, with an optimal wrap angle difference is about 20°.

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“…Wittrock, Elfert, and Hehn, respectively, optimized the SRV4 compressor with a relative inducer tip Mach number of 1.5, [22][23][24][25] and the results showed that a forward sweep leading edge reduced the loss due to the shock wave in front of the leading edge in the SRV4 compressor. He-xiao carried out numerical simulations and theoretical deductions on a transonic impeller with twin splitters 26 and summarized that the leading edge forward sweep of the main blade improved the loading distribution and shock wave and reduced the loss of the impeller.…”

Section: Introductionmentioning

confidence: 99%

The flow mechanism of the shock structure and secondary flow control in transonic centrifugal compressors with leading edge sweep

Han

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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Limitations still exist in the research on the effects of leading edge sweep on transonic centrifugal compressors. The lack of understanding of this mechanism also leads to confusion regarding the magnitudes of the performance changes that occur due to the use of leading edge sweep. According to a detailed numerical simulation verified by experiments on two different compressors, the effect and flow mechanism of leading edge sweep on transonic centrifugal compressors were investigated in detail to alleviate the confusion as clearly as possible. The conclusions show that leading edge sweep has different impacts on shock waves at different positions; a forward sweep leading edge can weaken the strength of the shock wave in front of the leading edge, while a backward sweep leading edge can weaken the strength of the passage shock wave that is swallowed in the blade passage. The improved compressor performance attributed to leading edge sweep is due to the weakening of the shock waves and the interaction between the shock waves and the secondary flow of the inducer tip. Furthermore, the intensity of the inducer tip secondary flow influences the potential for improved performance induced by using sweep leading edges in transonic centrifugal compressors. This study provides a valuable reference for applying leading edge sweep to existing transonic centrifugal compressors or future advanced centrifugal compressor designs.

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Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

Cited by 12 publications

References 42 publications

Optimization of a Centrifugal Compressor Using the Design of Experiment Technique

Optimization of a Centrifugal Compressor Using the Design of Experiment Technique

Investigation on the Impact of Trailing Edge Stacking Styles on Hydraulic Performance in the Multistage Submersible Pump Space Diffuser

The flow mechanism of the shock structure and secondary flow control in transonic centrifugal compressors with leading edge sweep

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