Optimized inlet geometry of a laidback fan-shaped film cooling hole – Experimental study of film cooling performance

Fraas, Marc; Glasenapp, Tobias; Schulz, Achmed; Bauer, Hans‐Jörg

doi:10.1016/j.ijheatmasstransfer.2018.09.035

Cited by 36 publications

(5 citation statements)

References 32 publications

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“…They found that despite the creation of negative vortices and jet vortices in the internal crossover flow resulting from the simulation of the flow in the turbine blade environment, the reuse of these end wall currents affects the film cooling effectiveness. Fraas et al [12] experimentally studied the film cooling performance improvement by using an optimized cooling hole inlet geometry. The results showed that the cooling hole inlet geometry tremendously affects cooling performance.…”

Section: Introductionmentioning

confidence: 99%

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Sidik

Kianpour²

2022

ARASET

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The major effects of cylindrical and spherical trenched cooling holes with distance between the hole surface and the combustion chamber panel and the filler diameter on the spherical hole contact surface and the panel surface H=0.3,R=D/2=0.1, H=0.3, R=D/2=0.2 and H=0.3, R=D/2=0.3 cm at BR=3.18 on the film cooling effectiveness near the combustor end wall surface is an important subject to study in details. In this research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analysed with a commercial finite volume package FLUENT 6.2.26. The analyses were done with RANS turbulence model on internal cooling passages. The combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. In comparison with the baseline case, the application of trenched holes increased the effectiveness of film cooling up to 47% near the wall surface and an average of 35% in depth of combustor simulator .

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Section: Introductionmentioning

confidence: 99%

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Sidik

Kianpour²

2022

ARASET

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“…High-resolution infrared measurements were used to study the inlet geometry of a laidback fan-shaped film cooling hole [8]. The comparisons showed that the inlet geometry of the cooling hole significantly affected cooling performance.…”

Section: Introductionmentioning

confidence: 99%

Mesh sensitivity of RANS simulations on film cooling flow

Jiang

Murray

Mare

et al. 2022

International Journal of Heat and Mass Transfer

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“…They may, however, compromise the airfoil structural integrity and aerodynamic efficiency. Some studies on discrete film holes include traditional cylindrical holes [3], laidback fanshaped holes [4][5][6][7][8][9], tripod holes [10][11][12][13][14], holes with sister holes [10][11][12][13][14][15][16][17][18], curved diffusion holes [19], and diffusion holes with different exit area geometries [20]. In this paper, we will study a new trench geometry, both experimentally and numerically, and discuss and compare the results.…”

Section: Introductionmentioning

confidence: 99%

Film Effectiveness Downstream the Trenches with Tilted Target Wall

Fan

Taslim

2022

International Journal of Rotating Machinery

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Film cooling is a commonly-accepted effective way to protect the gas turbine hot sections from the high temperature products of the combustion chamber. Numerous film hole geometries have been the subject of investigation by many researchers over the past three decades with the aim of keeping the target wall under the maximum allowable temperature with the least amount of precious cooling air and minimum aerodynamic losses. In this study, we are proposing a new trench geometry that is fed by 30°-inclined embedded circular film holes entering from the trench sidewall. The cooling jets impinge on the opposite wall of the trench which is tilted towards the jets and then is pushed over the coverage wall by the main flow. Three trench geometries with the same exit area and tilt angles (the angle between the trench side- and top-wall) of 75°, 90°, and 105° degrees are tested for three blowing ratios of 0.5, 0.75, and 1.0, and the film effectiveness results are compared using the adiabatic pressure sensitive paint technique. CFD analyses are also performed using the realizable k − ε turbulence model with the enhanced wall function option. Major conclusions of this study were that the trench geometry with the trench tilt angle of 75°, corresponding to the smallest trench volume, had the best performance at the lowest blowing ratio, and good agreement was observed between the CFD and test results.

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Optimized inlet geometry of a laidback fan-shaped film cooling hole – Experimental study of film cooling performance

Cited by 36 publications

References 32 publications

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Mesh sensitivity of RANS simulations on film cooling flow

Film Effectiveness Downstream the Trenches with Tilted Target Wall

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