Improving film cooling performance by using one -inlet and double-outlet hole

Li, Guangchao; Zhang, Wei

doi:10.1007/s11630-010-0405-x

Cited by 11 publications

(3 citation statements)

References 25 publications

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“…Enhanced film cooling effectiveness was obtained by the new design compared to the base line case, the circular scheme. A similar design was proposed by Li and Zhang [12]. The scheme they proposed is a circular scheme with one inlet and double outlet, Fig.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Effect of Louver Scheme Internal Bend and Exit Shape on the Film Cooling Performance over a Flat Plate

Hassan

Elnady

2015

International Conference on Aerospace Sciences and Aviation Tec

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This paper presents experimental investigations of the effects of the presence of an internal 90 o bend and the design of the scheme exit on the film cooling performance of the louver scheme over a flat plate using the transient Thermochromic Liquid Chrystal (TLC) technique. The Louver scheme is a shaped scheme with an internal 90 o bend, circular hole followed by a horizontal slot, which adds the impingement cooling benefits to the enhanced film cooling performance of shaped schemes. The louver film cooling scheme was manufactured in the present study with two different exit designs. The first is characterized with straight interfaces between the scheme and the test surface and the second has curved interface lines. Meanwhile, a third scheme was manufactured with the same exit shaped of the louver with curved interface lines, but without the internal 90 o bend. The film cooling performance of the proposed designs was investigated at three different blowing ratios, 0.5, 1.0 and 1.5, a density ratio of 0.93, a Reynolds Number of 1.24E+5, based on the free stream velocity and the main duct hydraulic diameter, and a turbulence intensity of 8.5. The blowing ratio is calculated based on the base diameter of the louver scheme and the same coolant amount is supplied to all cases. The investigations showed that the scheme exit design has a significant effect on the resulting effectiveness as it affects the interaction nature between the main and the secondary streams. This was clear during the investigations through the enhanced effectiveness performance downstream the louver scheme with curved exit design, compared to the louver with straight exit. Also, adding a 90 o internal bend to the shaped scheme design for impingement cooling purposes does not have a contribution on the scheme film cooling performance. Changing the film cooling scheme design did not affect the resulting heat transfer coefficient distribution significantly. This was attributed to the small change in the supplied coolant mass due to using the scheme base diameter for blowing ratio calculations.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Effect of Louver Scheme Internal Bend and Exit Shape on the Film Cooling Performance over a Flat Plate

Hassan

Elnady

2015

International Conference on Aerospace Sciences and Aviation Tec

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“…Park et al [6] presented the control of vortex flows by using forward and backward injection jets with various vortex intensities and hole dispositions to increase FE. Li and Zhang [7] numerically analyzed the effect of the geometry of the hole on the FE of a hole under trunk-branch shape with various M. The results showed that the FE is improved at M = 0.5. Li et al [8] numerically investigated the effect of the aperture ratios and injection angles of sister-shaped holes on FE.…”

Section: Introductionmentioning

confidence: 99%

Effect of Two-Head Flared Hole on Film Cooling Performance over a Flat Plate

Nguyen

Dinh

et al. 2021

Aerospace

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Film cooling is commonly utilized in turbine blades to decrease the temperature of the air stream from the combustion chamber that contacts directly with the blades. The shape of a cylindrical hole (CH) with the geometrical variations at inlet and outlet ports was examined using the 3D Reynolds-averaged Navier–Stokes equations (RANS) with a shear stress transport (SST k − ω) turbulence model to study the effect of the two-head flared hole on film cooling effectiveness (FE) at high accuracy with a small y+ value. To assess the effect of the changes, each geometry of the hole was changed one after another while the other parameters were kept invariable at the test value (cylindrical hole). The numerical laterally averaged film cooling effectiveness (ηl) of the CH case was validated and compared to the experimental data. The simulation results with the two-head flared hole indicated that most of these shape changes increase the FE as compared to the CH case. In particular, the maximum spatially averaged film cooling effectiveness (ηs) with hole shape expanded along the flow direction at the outlet port reached 60.787% in comparison to the CH case.

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“…Generating vortex technique is primarily a flow control technique whose effect in mitigating the CRVP action depends on the generated vortex location and strength. In this technique, the common anti-vortex generators include the use of chevron as shown by Abdala and Elwekeel [5], one-inlet double-outlet hole as presented by Li and Zhang [6], backward injection holes as presented by Park et al [7], or ramp upstream of the injection holes as presented by Na and Shih. [8] and Zhou and Hu.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Effect of Dielectric Barrier Discharge Actuator (Dbda) on Film Cooling Performance Downstream a Circular Hole Scheme Over a Gas Turbine Vane Pressure Side

Abdelhares

Hassan

El-Dosoky

et al. 2018

The International Conference on Applied Mechanics and Mechanica

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This paper presents a numerical investigation of the effect of DBDA length on film cooling performance downstream a circular hole scheme over a gas turbine vane pressure side. The investigated scheme is that of a set of two DBDAs installed downstream a cooling jet injection hole to damp the effect of the Counter Rotating Vortex Pair (CRVP) accompanying the injected cooling jet. The simulation has been carried out assuming one row of circular holes of a diameter D spaced at 4.5 D in the cross-stream direction and inclined at 22 ⁰ with the vane pressure side surface. The actuators are located at 0.5 D downstream the injection hole and spaced at a distance = 0.25 D. Five cases of different electrode's length ranging from 1.5 D to 12 D have been investigated under different applied voltages in the range from 10 kV to 60 kV. In all those cases both the blowing and density ratios are assumed constant at values equal 1 and 2, respectively. Then, the effect of changing the blowing ratio on the performance has been studied for the case which exhibit optimum performance where maximum surface effectiveness is achieved for specific actuator length and applied voltage. The obtained results show that, for each considered actuator length, the surface average effectiveness was enhanced with the increase of the applied voltage to a certain limit where a maximum value was obtained, and then the effectiveness decreased with the increase of the voltage. The results indicate that this limit varies with the actuator length in such a way that, the longer the actuator the lower the voltage at which maximum surface average effectiveness occurs.

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Improving film cooling performance by using one -inlet and double-outlet hole

Cited by 11 publications

References 25 publications

Experimental Investigation of the Effect of Louver Scheme Internal Bend and Exit Shape on the Film Cooling Performance over a Flat Plate

Experimental Investigation of the Effect of Louver Scheme Internal Bend and Exit Shape on the Film Cooling Performance over a Flat Plate

Effect of Two-Head Flared Hole on Film Cooling Performance over a Flat Plate

Numerical Investigation of the Effect of Dielectric Barrier Discharge Actuator (Dbda) on Film Cooling Performance Downstream a Circular Hole Scheme Over a Gas Turbine Vane Pressure Side

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