Design optimization of axial slot casing treatment in a highly-loaded mixed-flow compressor

Ba, Dun; Zhang, Qian‐Feng; Du, Juan; Li, Zhihui; Zhang, Hongwu; Nie, Chaoqun

doi:10.1016/j.ast.2020.106262

Cited by 30 publications

(6 citation statements)

References 15 publications

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“…The results of SM also illustrate this point that the SM of ORI, SES, SEI and CCT schemes are 10.8%, 16.2%, 10.9% and 25.5%, respectively. In general, the stable operating range of the compressor is expected to be extended with SES at the cost of decreasing the compressor efficiency [33], and the effect of injection is far from satisfactory in terms of the performance curve. The CCT scheme shows the best comprehensive performance considering both stability and efficiency.…”

Section: Overall Performancementioning

confidence: 99%

Analysis of Impact of a Novel Combined Casing Treatment on Flow Characteristics and Performance of a Transonic Compressor

et al. 2022

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To reduce the negative impacts of stall and surge on compressor performance, a novel combined casing treatment (CCT) structure with axial skewed slots and injection groove is proposed in this paper. The aerodynamic performance, as well as the mechanisms of loss generation, of a transonic axial compressor with NASA Rotor 67 are investigated numerically. The simulation results indicate that, compared with individual casing treatment method, the CCT works effectively with regard to operation performance. The stall margin (SM) is increased by 14.7% with 1.12% decrease in the peak efficiency. The interaction of axial skewed slots and injection groove can be explained by the enhancement of exchange flow in slots and axial motion of fluid. As a result, the leakage flow near the blade tip is eliminated and the flow separation is further suppressed. What is more, an analysis of entropy generation is also conducted. The results reveal that the effect of CCT on loss reduction mainly concentrates in the tip part of the blade, with the loss decrease about 14.46% compared with the original rotor. The best control effect can be expected by appropriate match between geometrical parameters of axial skewed slots and mass flow rate of injection from the parameter analysis.

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Section: Overall Performancementioning

confidence: 99%

Analysis of Impact of a Novel Combined Casing Treatment on Flow Characteristics and Performance of a Transonic Compressor

et al. 2022

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“…Alone et al 19 and Zhang et al 20 respectively conducted research on the position and porosity of axial slot. Furthermore, Ba et al 21 adopted genetic algorithm to optimize three kinds of axial slot with different meridional shapes. The self-recirculating passage, taking advantage of the pressure difference in rotor passage, suctions the fluid downstream of the rotor and jets this part of the fluid upstream of the rotor.…”

Section: Introductionmentioning

confidence: 99%

Impact of the ending position of controllable speed casing on the flow stability in a transonic compressor rotor

Zhao

Zhong

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The structure of casing treatment has a significant influence on the stability expansion effect. The ending position of the rotatable ring is one of the important structural parameters in the controllable speed casing. The impact of ending position of the rotatable ring rotating at the same speed as the rotor on the stability expansion and stability expansion mechanism was studied in this paper. The results show that, when the ending position of rotatable ring expands downstream in the range of 20% to 60% axial chord length, because of the improvement in the tip leakage vortex trajectory and main flow/leakage flow interface, the stability expansion effect rises gradually. The further downstream expansion of ending position from 60% axial chord length, however, has a slight impact on tip flow, bringing out a steady stability expansion effect around 52.5%. The best stability expansion effect of ending position occurs at 60% axial chord length where the stable operating margin increases by 53.5%.

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“…[8][9][10][11] Inspired by transonic axial compressors, researchers have gradually begun to study the influence and flow mechanism of leading edge sweep on the performance of transonic centrifugal compressors. 12,13 However, not only because the definition of sweep in centrifugal compressors is different from that in axial compressors but also due to the lack of research, no unified conclusion on the effect of sweep on internal flows in transonic centrifugal compressors exists.…”

Section: Introductionmentioning

confidence: 99%

“…8–11 Inspired by transonic axial compressors, researchers have gradually begun to study the influence and flow mechanism of leading edge sweep on the performance of transonic centrifugal compressors. 12,13…”

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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Design optimization of axial slot casing treatment in a highly-loaded mixed-flow compressor

Cited by 30 publications

References 15 publications

Analysis of Impact of a Novel Combined Casing Treatment on Flow Characteristics and Performance of a Transonic Compressor

Analysis of Impact of a Novel Combined Casing Treatment on Flow Characteristics and Performance of a Transonic Compressor

Impact of the ending position of controllable speed casing on the flow stability in a transonic compressor rotor

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

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