Impact of the Dimple-textured Surface on Pneumatic Performance of Compressor Cascades

LYU Huilin; YAN Guangwen; XU Jinting

doi:10.16490/j.cnki.issn.1001-3660.2026.05.019

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Surface Technology ›› 2026, Vol. 55 ›› Issue (5) : 235-245. DOI: 10.16490/j.cnki.issn.1001-3660.2026.05.019

Friction, Wear and Lubrication

Impact of the Dimple-textured Surface on Pneumatic Performance of Compressor Cascades

LYU Huilin^a, YAN Guangwen^a, XU Jinting^a,b,*

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Abstract

The work aims to reduce flow loss on the surface of aeroengine compressor blades. The research method combining numerical simulation and wind tunnel test was adopted to study the impact of the dimple-textured surface on pneumatic performance of axial compressor cascades. First of all, the numerical simulation model suitable for turbulent flow on the smooth/non-smooth cascade surface was established by computational fluid dynamics (CFD) technique. By carrying out the cascade wind tunnel test in the transonic test platform, experimental verification of the numerical method was completed. Then, the numerical simulation experiments were carried out. The effect of the position, spacing and size of dimples on total pressure flow loss of cascades with different profiles was analyzed by variable-controlling approach. The effect rules of the dimple parameters on pneumatic performance of cascades were revealed. The decrease rate of flow loss in total pressure of models with different dimple parameters was calculated and the optimal range of dimple parameters with better loss reduction effect was proposed. Finally, based on the simulation results, with the dimple parameters as the independent variables and the loss reduction rate as the response variable, the inverse model of the dimple parameter domain under the constraint of aerodynamic performance was established. The layout scheme of dimples with the best aerodynamic performance was proposed by the response surface analysis. The results showed that the range of dimpled surface with loss reduction effect was gradually expanding on cascades with different profiles cut from tip to root of the compressor blade and the starting position of the effective interval was gradually approaching the leading edge of the blade. The best loss reduction effect was achieved by arranging dimples on Cascade 4 taken from the blade root. The numerical calculation results showed that when dimples were arranged near the leading edge of the cascade whose profile was taken from the blade root and the spanwise spacing S was 2.4-2.6 mm or 3-3.4 mm, the radius r was 0.5-0.75 mm, the depth to diameter ratio was 0.15 or 0.45, the loss reduction effect of the non-smooth cascade was better and an optimal loss reduction rate of 11.50% was achieved. The optimal layout scheme of dimples was calculated based on the inverse model. At r=0.60 mm, h/d=0.45 and S=2.4 mm, the loss reduction effect of the non-smooth cascade was the best. The loss reduction rate predicted by the reverse calculation model and calculated numerically reached respectively 11.62% and 12.68%. Compared with the results of the previous simulation experiments, the loss reduction rate increased by 10.26%. Dimples increase the disturbance of the wall, because the reverse rotating vortices in dimples can draw the outer main fluid into the boundary layer, which augments near-wall momentum while inducing the transition in advance. As a result, the boundary layer has sufficient kinetic energy to resist the reverse pressure gradient without separation. Dimples effectively suppress the generation of the separation bubble, reduce the total pressure flow loss caused by separation of the boundary layer and improve aerodynamic performance of the cascade.

Key words

compressor cascade / dimples / inverse model / aerodynamic performance / boundary layer separation / flow loss

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LYU Huilin, YAN Guangwen, XU Jinting. Impact of the Dimple-textured Surface on Pneumatic Performance of Compressor Cascades[J]. Surface Technology. 2026, 55(5): 235-245

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Funding

National Key Research and Development Program of China (2020YFA0713702); Key Project of the Basic Science Center for Aero-engine and Gas Turbine (P2023-B-IV-002-001); Natural Science Foundation Program of Liaoning Province (2024-MSBA-21)