Numerical simulation of the effect of plasma aerodynamic actuation on improving film hole cooling performance

Yu, Jinlu; He, Lin; Zhu, Yifei; Ding, Wei; Wang, Yu-qian

doi:10.1007/s00231-013-1157-4

Cited by 28 publications

(18 citation statements)

References 12 publications

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“…C C Wang and Subrata Roy [19,20] propose a possible way to improve film-cooling performance by putting a single SDBD actuator at the exit of hole. Jin-lu Yu and Li-ming He [21] studied the effect of actuator location, input power and actuator number on the film-cooling performance. All the studies revealed that employing the structure of film-cooling hole with SDBD actuator is an effective way to improve film-cooling performance.…”

Section: Introductionmentioning

confidence: 99%

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Dai

Yang

et al. 2015

International Journal of Heat and Mass Transfer

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Section: Introductionmentioning

confidence: 99%

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Dai

Yang

et al. 2015

International Journal of Heat and Mass Transfer

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“…10,11 Jin-Lu Yu researched the effect of actuator number, power and location on the performance of film cooling in two-dimensional simulation. 12 However no case of relative experimental study has been reported yet, and further studies are needed on the influence of plasma aerodynamic actuation on the structure of the JICF field.…”

Section: Introductionmentioning

confidence: 99%

An experimental study of plasma aerodynamic actuation on a round jet in cross flow

Dai

Yang

et al. 2015

AIP Advances

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The present paper is performed on the effect of plasma aerodynamic actuation on a round jet in cross flow field with a low Reynolds number by using smoke visualization. The actuator is constituted by an electrode pair separated by a dielectric Al2O3 sheet. Several AC supply conditions are utilized. The experimental result shows a closing-in tendency of the jet flow toward the wall after being induced by plasma aerodynamic actuation, and such tendency is increasingly intensified as the actuation voltage increases. Numerical simulation is also performed. The simulation results show that an induced vortex pair is generated by plasma aerodynamic actuation near the wall flow field. The rotation direction of the induced vortex pair reverses against the counter-rotating vortex pair generated by a round jet in a cross flow without plasma aerodynamic actuation. Then the strength and structural size of the counter-rotating vortex pair are significantly reduced, resulting in the intensified near-wall effect of the jet flow. Three electrode-typed actuators (straight, 150°-elliptic arc and 180°-elliptic arc with the same streamwise extent) are placed at the exit of round jet to research the influence of electrode structure on jet in cross flow. The result shows that the longer the arc electrode surrounding the hole, the stronger the induced jet that flow near the wall is.

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“…Wang and Roy [11] investigated the effect of geometrical changes of DBDA located at the hole exit for improving film cooling performance. Yu et al [12] studied the film cooling performance with DBDA and reported that position, power input, and the numbers of DBDAs used have significant effects on film cooling effectiveness. Dai et al [13] used a pair of DBDAs to produce anti-vortex pair opposite to CRVP and investigated the influence of different geometrical parameters on the performance at different blowing ratios.…”

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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Numerical simulation of the effect of plasma aerodynamic actuation on improving film hole cooling performance

Cited by 28 publications

References 12 publications

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

An experimental study of plasma aerodynamic actuation on a round jet in cross flow

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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