Blade Lean and Tip Leakage Flows in Highly Loaded Compressor Cascades

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

doi:10.1007/s11630-021-1486-4

Cited by 6 publications

(1 citation statement)

References 19 publications

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“…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] ]. Notably, the aforementioned flow-control method in the tip-clearance area requires substantial modifications to the compressor structure and internal aerodynamic layout, resulting in higher costs.…”

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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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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Effect of vorticity transport on flow structure in the tip region of axial compressors

et al. 2022

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Numerical simulations are carried out to investigate the flow structure in the blade tip region of axial compressors. Various tip clearance heights and end wall motion conditions in a linear compressor cascade are studied to assess the effect of vorticity transport on the tip leakage flow (TLF). Moreover, the effect of vorticity transport on the TLF in a compressor rotor at different operating conditions is studied using delayed detached eddy simulation. The results show that the vorticity transport at both the blade tip and the end wall plays an important role in the roll-up and evolution of the tip leakage vortex (TLV), resulting in great impacts on the loss and stability of the TLV. It is found that the TLV is composed of a two-layer structure. The inner vortex core region formed by the vorticity transport from the blade tip shear layer to the TLV has a great effect on the strength and loss of the vortex, and the structure of the outer shear layer is altered by the secondary vortex formed by the vorticity transport from the end wall shear layer and thus affects the stability of the TLV. By the mechanism of the vorticity transport, the effects of the clearance height, the end wall motion, and the non-uniform clearance as a control method can be explained uniformly. The new understanding of the TLF structure and the vorticity transport mechanism helps to improve the performance of axial compressors by controlling the vorticity transport of the TLF.

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Blade Lean and Tip Leakage Flows in Highly Loaded Compressor Cascades

Cited by 6 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

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

Effect of vorticity transport on flow structure in the tip region of axial compressors

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