Experimental investigations on the effects of inclination angle and blowing ratio on the flat-plate film cooling enhancement using the vortex generator downstream

Song, Liming; Zhang, Chao; Song, Yingjie; Li, Jun; Feng, Zhenping

doi:10.1016/j.applthermaleng.2017.03.089

Cited by 51 publications

(10 citation statements)

References 29 publications

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“…Eckert 22 , Pederson 23 , and Schmidt 24 had performed experiments under the same conditions, and corresponding results are attained. Moreover, based on detailed experimental investigation on flow mechanism and thermal characteristics of film cooling, Song 25 researched the impact of blowing ratio and inclination angle on the film cooling effectiveness enhancement by using vortex generator. Numerical simulations are performed by LES in this manuscript, and the results are displayed in Fig.…”

Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Investigations on the effect of different influencing factors on film cooling effectiveness under the injection of synthetic coolant

Chang

Duan

et al. 2021

Sci Rep

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By combining the synthetic jet and film cooling, the incident cooling flow is specially treated to find a better film cooling method. Numerical simulations of the synthetic coolant ejected are carried out for analyzing the cooling performance in detail, under different blowing ratios, hole patterns, Strouhal numbers, and various orders of incidence for the two rows of holes. By comparing the flow structures and the cooling effect corresponding to the synthetic coolant and the steady coolant fields, it is found that within the scope of the investigations, the best cooling effect can be obtained under the incident conditions of an elliptical hole with the aspect ratio of 0.618, the blow molding ratio of 2.5, and the Strouhal number St = 0.22. Due to the strong controllability of the synthetic coolant, the synthetic coolant can be controlled through adjusting the frequency of blowing and suction, so as to change the interaction between vortex structures for improving film cooling effect in turn. As a result, the synthetic coolant ejection is more advisable in certain conditions to achieve better outcomes.

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Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Investigations on the effect of different influencing factors on film cooling effectiveness under the injection of synthetic coolant

Chang

Duan

et al. 2021

Sci Rep

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“…It was found that the downstream vortex generator can improve cooling effectiveness by generating near-wall vortices opposite to the CRVP. The experimental work by Song et al [15] also revealed the down-wash effect of the induced vortices by the delta-shaped vortex generator at blowing ratios ranging from 0.5 to 1.5. In order to expand the lateral coolant coverage and alter the vortex structure around the hole, An et al [16] proposed a streamlined crescent-shaped block downstream the hole.…”

Section: Introductionmentioning

confidence: 93%

“…In the review of the literature [7][8][9][10][11][12][13][14][15][16][17], several specific block shapes were opposed. Except for the block shape [7][8][9][10][11][12][13][14][15][16][17], the height of the block also has a great impact on the cooling performance and aerodynamic loss. Based on the results in [9][10][11], higher protrusions or vortex generators upstream the hole resulted in better cooling performance but also higher aerodynamic loss.…”

Section: Introductionmentioning

confidence: 99%

Influence of streamwise position of crescent-shaped block on flat-plate film cooling characteristics

Zhang

Wang

2019

J Braz. Soc. Mech. Sci. Eng.

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Film cooling injection from discrete circular holes is widely used in gas turbines to reduce the heat load of the turbine blades. Placing a special designed structure upstream or downstream, the circular hole has been proven to be a new effective way to improve cooling effectiveness in recent years. In the present study, numerical investigations were performed on a row of circular holes over a flat plate with crescent-shaped blocks. Totally seven configurations without block, with blocks located at six streamwise positions including 6 times, 5 times, 4 times of hole diameter upstream, and 0.5 times, 1.5 times, 2.5 times of hole diameter downstream at blowing ratios of 0.5-1.5 were tested symmetrically. The Reynolds-averaged Navier-Stokes equations with the k-ω shear-stress transport model were solved. Flow fields, cooling effectiveness and aerodynamic losses were analyzed in detail. Although with different generation mechanism, additional vortex pair opposite to the counter-rotating vortex pair was generated by placing either an upstream or downstream block, which could finally improve the coolant lateral coverage and thus cooling effectiveness. The cooling performances and aerodynamic losses between configurations without block and with blocks at six streamwise positions were then compared. Finally, the optimal streamwise position of the block was recommended at various blowing ratios.

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“…Because of the high importance and widespread application of film cooling, research into its various aspects has seen a tremendous increase in the last 10–15 years. The publications relating directly or indirectly to film cooling are too numerous to recount here, and they studied the effects of film hole internal fluid dynamics, interactions with the mainstream gas flow, vortex production, hole shaping, orientation, spacing, hole length-to-diameter ratio, density ratio and blowing strength, momentum flux ratio, mainstream turbulence intensity and so on [ 8 , 9 , 10 , 11 , 12 , 13 , 14 , 15 ]. A series of internal cooling methods such as impingement cooling have been used in the turbine vane leading edge.…”

Section: Introductionmentioning

confidence: 99%

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Mei

Zou

et al. 2019

Entropy

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Numerical calculation of conjugate heat transfer was carried out to study the effect of combined film and swirl cooling at the leading edge of a gas turbine vane with a cooling chamber inside. Two cooling chambers (C1 and C2 cases) were specially designed to generate swirl in the chamber, which could enhance overall cooling effectiveness at the leading edge. A simple cooling chamber (C0 case) was designed as a baseline. The effects of different cooling chambers were studied. Compared with the C0 case, the cooling chamber in the C1 case consists of a front cavity and a back cavity and two cavities are connected by a passage on the pressure side to improve the overall cooling effectiveness of the vane. The area-averaged overall cooling effectiveness of the leading edge () was improved by approximately 57%. Based on the C1 case, the passage along the vane was divided into nine segments in the C2 case to enhance the cooling effectiveness at the leading edge, and was enhanced by 75% compared with that in the C0 case. Additionally, the cooling efficiency on the pressure side was improved significantly by using swirl-cooling chambers. Pressure loss in the C2 and C1 cases was larger than that in the C0 case.

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Experimental investigations on the effects of inclination angle and blowing ratio on the flat-plate film cooling enhancement using the vortex generator downstream

Cited by 51 publications

References 29 publications

Investigations on the effect of different influencing factors on film cooling effectiveness under the injection of synthetic coolant

Investigations on the effect of different influencing factors on film cooling effectiveness under the injection of synthetic coolant

Influence of streamwise position of crescent-shaped block on flat-plate film cooling characteristics

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

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