Blade-end treatment to improve the performance of axial compressors: An overview

Zheng, Xinqian; Li, Zhihui

doi:10.1016/j.paerosci.2016.09.001

Cited by 22 publications

(4 citation statements)

References 52 publications

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“…There is a trade-off between the improved endwall region flows and the degraded mid-span flows. 36 Because of the high performance at mid-span area, the increasing blade loading does not deteriorate the flow. However, if the dihedral angle is too large, it will cause large separation in mid-span area.…”

Section: Results and Analysesmentioning

confidence: 99%

Investigation of endwall treatment and shock control in a five-stage axial compressor

Yang

Zheng

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Multistage axial compressor is one of the key components in aero engines and gas turbines. In this paper, a five-stage axial compressor was studied to improve the efficiency. First, the loss analyses of the datum compressor were performed. The results showed that front rotors and rear stators have higher loss. Based on the loss analyses, the corresponding flow controls were introduced. The endwall treatment was performed with the rear stators, S3, S4, and S5, by end-bow, which changed the blade loading and reduced the loss due to endwall boundary layer. The efficiency of the datum compressor was increased by 0.5%. Based on the improved redesign of rear stators, shock control was introduced to front rotors, R1 and R2, characterized by sweep, which changed the shock structure and decreased the shock-induced loss and shock-tip leakage interaction. Coupled between endwall treatment and shock control, compared to the datum compressor, the efficiency, peak pressure ratio, and choked mass flow were increased by 1.1%, 1.1%, and 1.2%, respectively. At off-design speeds, the performances were also improved, which implies the flow controls for design speed remain effective in a range of off-design speeds. The reliability of the redesigned compressor was validated by stress and mode analyses.

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Section: Results and Analysesmentioning

confidence: 99%

Investigation of endwall treatment and shock control in a five-stage axial compressor

Yang

Zheng

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Section: Introductionmentioning

confidence: 99%

“…Compressor blade design is a method that considers sufficient stall margin in advance at the beginning of compressor design, for example, complex blade sweep technology 3 and blade-end treatment. 12 Casing treatment (CT) has been shown to be successful in extending compressor stall margin with inevitable efficiency penalty. Up to now, various casing treatment configurations such as groove-type, 13 slot-type, 14,15 and self-circulation 16,17 have been developed.…”

Section: Introductionmentioning

confidence: 99%

Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

Chi,

Chu,

Zhang

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Casing treatment and three-dimensional blade design are effective techniques to remedy the deficiency of compressor stability margin, yet their combined effects on compressor performance are seldom studied. With the help of URANS simulations, this paper explored the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor. Compared with the configurations of single sweep and single casing treatment, the combined configuration presented an outstanding advantage for improving compressor performance. For compressor overall performance, the stall margin improvement of combined configuration was up to 11.8%, larger than single forward sweep and single casing treatment. Meanwhile, peak efficiency penalty of combined configuration (−1.02%) was significantly lower than that of single casing treatment. Under the effect of casing treatment, the results showed that the pulsating axial velocity could effectively delay the interface of the tip leakage flow and main flow, preventing the overflow of tip leakage flow. The distributions of blockage coefficient and loading coefficient indicated that combined configuration was more effective due to tip unload by casing treatment and blockage resistance ability by forward sweep. Furthermore, the spatial and temporal evolutions of axial velocity at slot opening surface were discussed in detail. Compared with the single casing treatment, higher positive axial velocity excitation and smaller range of negative axial velocity were introduced by combined configuration, which contributed to better stability enhancement.

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“…Its application has been widely spread from compressors to turbines and from rotors to stators [10], especially applied to blade ends to improve the endwall flowfields [11]. For compressor rotors, a detailed survey [12] suggested that forward swept blades improved the efficiency and extended the stall-free operating range by reducing the near-wall and tip clearance losses, as well as controlling the secondary flows and radial migration of high-loss fluid.…”

Section: Introductionmentioning

confidence: 99%

Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

Zheng

2017

Applied Sciences

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Featured Application: The mechanism for the optimal sweep angle of centrifugal compressors has been proposed, which benefits high-efficiency designs of centrifugal compressors for turbocharger and gas turbine engine applications.Abstract: Transonic centrifugal compressors with high performance are required in the oil and gas industries, modern gas turbine engines, and turbochargers. The sweep of the blades is one of the crucial features that have a significant influence on their performance. This paper numerically investigates mechanisms by which sweep affects the performance of a transonic impeller with twin splitters. Sweep is defined as scaling up or down the shroud chord, and the variation range of the sweep angle has been chosen from −25 to +25 • . In the current case, results show that the variation of choke mass flow rate, pressure ratio, and efficiency value is around 1%. If the centrifugal compressor has a higher pressure ratio or a higher front loading, the sweep effect on compressor performance will be even stronger. The essential aerodynamic effect of sweep is the spanwise redistribution of the front loading, resulting in effects on the shock structure, the tip leakage vortex, and the flow separation. On the shroud section, forward sweep restricts the front loading, the shock strength, and the tip leakage vortex, which reduces the loss near the casing. On the hub section, aft sweep suppresses the front loading and the flow separation, which reduces the loss near the hub. It is the delicate balance between controlling the loss near the hub and the loss near the casing that determines the optimal sweep angle design.

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Blade-end treatment to improve the performance of axial compressors: An overview

Cited by 22 publications

References 52 publications

Investigation of endwall treatment and shock control in a five-stage axial compressor

Investigation of endwall treatment and shock control in a five-stage axial compressor

Study on the combined influence of aerodynamic sweep and casing treatment in a transonic compressor rotor

Mechanisms of Sweep on the Performance of Transonic Centrifugal Compressor Impellers

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