Combined flow control with full-span slot and end-wall boundary layer suction in a large-camber compressor cascade

Wang, Hejian; Mao, Xiaochen; Liu, Bo; Qing, Yanshan

doi:10.1016/j.ast.2021.107121

Cited by 11 publications

(3 citation statements)

References 19 publications

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“…Slotted blade technology has also been used for gas flow control and underwater airfoil drag reduction (Xie et al 2020). Finally, research has also been conducted on the combination of slotted blade technology and other flow control technologies to achieve reasonable flow control (Hu et al 2018b, Wang 2021).…”

Section: Introductionmentioning

confidence: 99%

Impact of Slots on the Aerodynamic Performance of the Variable Inlet Guide Vane Cascade of a Centrifugal Compressor

Xin

Liu²,

Zhao³

et al. 2023

JAFM

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This study reconstructed the flow field of a symmetrical variable inlet guide vane in a centrifugal compressor through the passive control method of vane slots. Based on the high-fidelity numerical simulation model verified by experiments, the influence of different slot forms on the flow field was investigated, and the passive control mechanism was revealed. The results demonstrated that the vane slot method can effectively suppress the suction surface separation and broaden the range of low-loss incidence angles. Overall, the 50_30 slotted vane achieves the best flow field control, with a 65.6% reduction in the total pressure loss coefficient and a 2.3° reduction in the deviation angle, respectively, at a 25° incidence angle. The linear characteristics of the pre-swirl grade variation curve with variable inlet guide vane incidence angles are also improved. Furthermore, changing the slot outlet angle has the most significant influence on the aerodynamic performance as it changes the throat width of the location, thereby affecting the flow rate and momentum of the jet. Finally, the impact of the velocity varies in the first self-similarity region on the slotted vane. The results indicate that, in contrast to the baseline vane, the suppression effect of the slot jet on the flow separation improves with the inlet velocity, whereas the deviation angle of the slotted vane declines with the inlet velocity. Meanwhile, the higher the incoming flow velocity, the better the slotted jet can inhibition of flow separation.

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Section: Introductionmentioning

confidence: 99%

Impact of Slots on the Aerodynamic Performance of the Variable Inlet Guide Vane Cascade of a Centrifugal Compressor

Xin

Liu²,

Zhao³

et al. 2023

JAFM

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“…The loss reduction was 41.9% when the optimal combined scheme was applied. Wang et al 18 investigated a combined scheme with passive and active suction slots in a high loaded subsonic compressor. They founded that the compressor performance was improved by changing the vortex development and delaying the boundary layer separation.…”

Section: Introductionmentioning

confidence: 99%

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Li,

Mu,

Luo

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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A numerical investigation is conducted to explore the potential of combined slot suction in controlling the shock wave and flow separation in a transonic compressor cascade. The three slots in the combined scheme are arranged in different directions on the suction surface and endwall. The locations are determined by the shock wave and separation point in the baseline cascade. Based on these locations, two combined schemes and three single schemes are provided to explore the control mechanism. For each suction scheme, five bleed mass ratios are examined at the same inlet Mach number. The results suggested that the cascade throughflow loss could be decreased by three single schemes. However, the cascade performance is improved slightly or even deteriorated when the losses generated by the suction are considered. The key reasons are the local effects of single scheme and the opposite trend between corner stall and the suction surface separation. Both corner stall and the suction surface separation are eliminated by the combined scheme with two slots, and the maximum reduction in throughflow losses is 75%. The new corner separation evolved from the horseshoe vortex limited the performance of combined scheme. When the bleed mass ratio excided 5%, the combined scheme with three slots is better than the two slots scheme in loss control. The reason is the improved endwall boundary layer and the eliminated new corner separation. By inducing the horseshoe vortex into the slot, the interaction of the two endwall slots eliminates the new corner separation.

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“…As the compressor load increases, the boundary layer near the endwall grows rapidly, which can lead to significant secondary flow loss and flow blockage and bring a significant impact on aerodynamic performance [ 20 ]. So far, many flow control methods have been proposed by scholars to improve the flow field near the endwall [ 20 , 21 , 22 , 23 , 24 , 25 , 26 , 27 , 28 ]. From previous research, we can find that it is of great significance to improve the flow field near the endwall by applying bowed blade modeling methods [ 20 , 21 , 25 , 27 , 28 ] and endwall blade modeling methods [ 20 , 22 , 23 , 24 , 25 ] in the blade design of highly loaded compressors.…”

Section: Introductionmentioning

confidence: 99%

Novel Optimization Design Methods of Highly Loaded Compressor Cascades Considering Endwall Effect

Liu

Chen

Li³

et al. 2022

Entropy

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The endwall effect has a great impact on the aerodynamic performance of compressor blades. Based on three conventional near-endwall blade modeling methods of bowed blade, endbend blade and leading-edge strake blade (LESB), two combined optimization design methods of highly loaded blades have been developed considering the endwall effect in the current study, i.e., the bowed blade combined with the LESB (bowed LESB blade) and the endbend blade combined with the LESB (endbend LESB blade). Optimization designs were conducted for a compressor cascade with low solidity by using the two combined modeling methods and the three conventional modeling methods, and the optimization results were compared and analyzed in detail. The results showed that the five optimization modelling methods could all improve the performance for the original cascade, and the optimized cascade with the bowed LESB modeling method has the best aerodynamic performance. The total pressure loss of the optimal bowed LESB cascade was only 40.3% of that in the original cascade while reducing the solidity of the original cascade from 1.53 to 1.25 and keeping the static pressure rise and diffusion factor at the same level as the original one. Among the optimal cascades, the radial migration height of the low-energy fluid and the corresponding vortex have great effects on the aerodynamic performance, and the optimal bowed LESB cascade is superior to the other optimal cascades in this aspect.

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Combined flow control with full-span slot and end-wall boundary layer suction in a large-camber compressor cascade

Cited by 11 publications

References 19 publications

Impact of Slots on the Aerodynamic Performance of the Variable Inlet Guide Vane Cascade of a Centrifugal Compressor

Impact of Slots on the Aerodynamic Performance of the Variable Inlet Guide Vane Cascade of a Centrifugal Compressor

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Novel Optimization Design Methods of Highly Loaded Compressor Cascades Considering Endwall Effect

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