Experimental investigations of the film cooling effectiveness of a micro-tangential-jet scheme on a gas turbine vane

Hassan, O.; Hassan, Ibrahim

doi:10.1016/j.ijheatmasstransfer.2013.02.001

Cited by 15 publications

(8 citation statements)

References 26 publications

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“…Figure 7(a) shows the distribution of Mach number over both the pressure side and suction side of the vane. It can be seen from this figure that the present computed results of the variation of Mach number with x/Cx for both vane sides are in very good agreement with the experimental results of Hassan and Hassan [18]. Also, Fig.7 (b) compares the present model results of the centerline effectiveness with the corresponding results of Sinha et al [4], Ito et al [16] and Walters and Leylek [19].…”

Section: Validation Of the Modelsupporting

confidence: 84%

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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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Section: Validation Of the Modelsupporting

confidence: 84%

“…In order to validate the accuracy of the present numerical model solutions, the Mach number distribution calculated for case-0, base-line case, Table 2, is compared with the experimental results of Hassan and Hassan [18] . Figure 7(a) shows the distribution of Mach number over both the pressure side and suction side of the vane.…”

Section: Validation Of the Modelmentioning

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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“…• The recent experimental work from Hassan et al [21] found that the micro-tangential-jet (MTJ) provided superior performance than shaped coolant exit scheme. The application of MTJ resulted in better lateral spreading of the coolant and penetrated longer distance without getting mixed.…”

Section: Advancement In Film Cooling Technologymentioning

confidence: 99%

“…Another experimental work from Sriram and Jagadeesh [13] observed that the array of micro jets results in better performance than the single jet and injection of coolant from the micro jets with low momentum did not provide significant changes in aerodynamic forces. The recent experimental work from Hassan et al [21] showed that the MTJ scheme performed much better than the shaped exit scheme model and they observed that the decay of effectiveness on the suction side was less than the pressure side of the turbine vane. The common conclusion from the micro film cooling is that the flow penetrates a long distance and use less amount of coolant.…”

Section: Micro Flow Behaviourmentioning

confidence: 99%

Numerical Analysis of Film Cooling from Micro-Hole

Balasubrammaniyan¹

2021

Preprint

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The performance of aircraft gas turbine engines mainly depends on performance of the turbine which expands the combusted air into the atmosphere. The turbine is a critical part which gets affected by the hot gas from combustor exhaust. So in order to enhance the performance of gas turbine engines, a proposed cooling type called film cooling is used for more than six decades. The current work is also an attempt to enhance the performance of the gas turbine engine by enhancing the film cooling performance. The film cooling performance was numerically calculated on a flat plate with micro-hole and compared the cooling performance from the macro-hole. The analysis was carried out for different blowing ratios and found that the coolant from micro-hole performs better in the vicinity region and also spreads well in the lateral direction. The vortex structure is also captured from the proposed turbulence model and discussed. The behaviour of micro flow inside the coolant pipe was also analyzed. The comparison between multiple micro-hole jets and discrete jets was also made and discussed.

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“…The calibration of the TLC is carried out every time the set-up is changed and intermediately between tests, every few days, to ensure that the camera and light positions did not changed. More details about the calibration procedure could be found in Hassan [20].…”

Section: Tlc Calibrationmentioning

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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Experimental investigations of the film cooling effectiveness of a micro-tangential-jet scheme on a gas turbine vane

Cited by 15 publications

References 26 publications

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

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

Numerical Analysis of Film Cooling from Micro-Hole

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

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