Computational Study on the Boundary Layer Suction Effects in the Supersonic Compressor Flow with a Bowed Blade

Cao, Zeyuan; Song, Cheng; Gao, Xi; Zhang, Xiang; Liu, Bo

doi:10.1007/s11630-022-1582-0

Cited by 12 publications

(2 citation statements)

References 19 publications

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“…This technology can be broadly categorized into active and passive control methods. Active control techniques include boundary-layer suction, end-wall air injection, and casing suction [ [5] , [6] , [7] ]. Passive flow-control methods include casing treatments, slotted blades, and curved/swept blades [ [8] , [9] , [10] , [11] ].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the influence of nonuniform tip clearance on rotor tip-clearance flow field structure

Zhang,

Li,

Cao

et al. 2024

Heliyon

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Section: Introductionmentioning

confidence: 99%

Numerical investigation on the influence of nonuniform tip clearance on rotor tip-clearance flow field structure

Zhang,

Li,

Cao

et al. 2024

Heliyon

Self Cite

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“…To solve this problem, scholars developed combined scheme to achieve a better control of flow separation. The research from Cao et al 17 investigated the effects of the combination between bowed blade and BLS on the shock structure in a supersonic stator. They found that the combined bleed leaded to a C-shaped shock wave.…”

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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Pitchwise casing treatment for effects of grooves on dynamics of vortices and loss of blade tip region of a compressor cascade

Cao

Yang²,

Gao³

et al. 2022

Aerospace Science and Technology

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Computational Study on the Boundary Layer Suction Effects in the Supersonic Compressor Flow with a Bowed Blade

Cited by 12 publications

References 19 publications

Numerical investigation on the influence of nonuniform tip clearance on rotor tip-clearance flow field structure

Numerical investigation on the influence of nonuniform tip clearance on rotor tip-clearance flow field structure

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

Pitchwise casing treatment for effects of grooves on dynamics of vortices and loss of blade tip region of a compressor cascade

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