An advanced impingement/film cooling scheme for gas turbines – numerical study

Immarigeon, A.; Hassan, Ibrahim

doi:10.1108/09615530610653091

Cited by 23 publications

(11 citation statements)

References 43 publications

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“…Figure 10 plots the centerline effectiveness and the spanwise averaged effectiveness using phenomenological model over the work surface. The computed centerline results for the baseline case (no force) compares reasonably with the experiment of Sinha et al 6 and two other previously reported numerical results [23][24] . We can see the centerline effectiveness decreases for the baseline case as the distance of downstream (x/d) increases due to the liftoff effect.…”

Section: Resultssupporting

confidence: 86%

Active Cooling of Turbine Blades using Horse-Shoe Plasma Actuator

Wang

Roy

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Section: Resultssupporting

confidence: 86%

Active Cooling of Turbine Blades using Horse-Shoe Plasma Actuator

Wang

Roy

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…We can see the centerline effectiveness decreases for the baseline case as the distance of downstream (x∕d) increases due to the liftoff effect. The result predicted by our model is similar to two other numerical predictions [29,30]. In Fig.…”

supporting

confidence: 92%

“…9 against a nondimensional ratio of x∕Md, where x is the downstream distance, M is the blowing ratio, and d is the circular pipe diameter. The computed centerline effectiveness results for the baseline case (with no actuation) compare reasonably with the experiment of Sinha et al [15] and two other previously reported numerical results [29,30] as shown in Fig. 9a.…”

supporting

confidence: 87%

“…As mentioned earlier, problem I focuses on understanding the basic influence of a horseshoe actuator on the surrounding flow under a near-quiescent condition (with a freestream velocity of 0.3 m∕s). For problem II, the baseline case is compared with Sinha et al's experimental data [15] and two other numerical works [29,30]. Other cases are scaled with different levels of plasma force density for improving film cooling effectiveness.…”

Section: Resultsmentioning

confidence: 99%

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Numerical Investigation of Three-Dimensional Plasma Actuation for Improving Film Cooling Effectiveness

Roy

Wang

2013

Journal of Thermophysics and Heat Transfer

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We numerically test a horseshoe plasma actuator for film cooling enhancement on a flat plate. We solve threedimensional plasma governing equations using the finite element based MIG flow code. The electric force density calculated from the plasma governing equations is then employed as a body force density into a finite volume based Navier-Stokes solver with standard turbulence models for controlling the flow. Such electric force influences attachment of the cold jet to the work surface by actively altering the three-dimensional flowfield in the vicinity of the actuator. We consider two problems related to film cooling. The first problem is to understand the influence of a horseshoe plasma actuator on a flowfield where the cooling jet and the bulk flow speeds are of the same order of the flow induced by plasma itself. The second problem is to validate a previously reported film cooling experiment with a single row of round cooling holes issuing at a 35 deg angle on a flat plate, and then predict any improvement due to plasma actuation. For a unit blowing ratio, the results are compared with the published experimental data and other numerical predictions. The numerical results show a progressive improvement of centerline effectiveness as the electric force density is increased from 0 (no force) to 8 MN∕m 3 (maximum). Specifically, an improvement of effectiveness well above 100% is predicted over the standard baseline design for the latest film cooling technology.

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“…Combining the jet impingement benefits and film cooling in one scheme, the Louver scheme was first proposed by Immarigeon and Hassan [15]. The Louver scheme is a shaped scheme with an internal 90 o bend, circular hole followed by a horizontal slot.…”

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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An advanced impingement/film cooling scheme for gas turbines – numerical study

Cited by 23 publications

References 43 publications

Active Cooling of Turbine Blades using Horse-Shoe Plasma Actuator

Active Cooling of Turbine Blades using Horse-Shoe Plasma Actuator

Numerical Investigation of Three-Dimensional Plasma Actuation for Improving Film Cooling Effectiveness

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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