Computation of leading edge film cooling from a CONSOLE geometry (CONverging Slot hOLE)

Guelailia, A.; Khorsi, Azzeddine; Hamidou, M.

doi:10.1134/s0869864316010042

Cited by 13 publications

(4 citation statements)

References 22 publications

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“…Two shapes of perforation are tested: converged slots and cylindrical perforations. Guelailia et al [5] conducted a numerical investigation to study the mass flow rate effect on heat transfer over a rotor blade of gas turbine. To improve film cooling performance, the converging slot holes are used instead of the cylindrical holes.…”

Section: Introductionmentioning

confidence: 99%

Effects of Crescent Shaped Block Width and Length on Flow Field and Film Cooling Performance

Guelailia¹,

Khorsi

Ahmed³

et al. 2023

Trends Sci

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Turbine blades and rocket nozzles can be efficiently protected from combustion chamber exhaust hot gases by film cooling technic. A crescent-shaped block placed downstream of the injection hole can significantly improve cooling effectiveness. The main objective of this research work is to investigate the inﬂuence of the crescent-shaped block length and width on film cooling effectiveness. ANSYS CFX was used to conduct analysis of a flat plate configuration with cylindrical holes. Nine configurations of the crescent shaped blocks were considered. For each case, the effect of blowing ratios (0.5 and 1) was investigated. The turbulence model shear stress transport (SST) is used for approximating turbulence. Good agreement was obtained by comparing the analysis results with the experimental data. The result indicated that block width variation has a considerable impact on film cooling performance. However, slight effect of block length on cooling effectiveness was obtained. Comparing all analyzed configurations, the best cooling effectiveness was reached for the model 9 (W = 3d, B = 1.5d). HIGHLIGHTS Rocket nozzles can be efficiently protected from combustion chamber exhaust hot gases by film cooling technic One of the latest techniques to optimize the overall performance of film cooling is adding an obstacle configuration downstream the coolant perforation Film cooling performance is considerably enhanced by placing a crescent shaped block downstream the injection hole The maximum enhancement in overall film cooling effectiveness using the optimal configuration (model 6: W = 2d, B = 1.5d) is about 252 % achieved at a blowing ratio of M = 1 GRAPHICAL ABSTRACT

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Section: Introductionmentioning

confidence: 99%

Effects of Crescent Shaped Block Width and Length on Flow Field and Film Cooling Performance

Guelailia¹,

Khorsi

Ahmed³

et al. 2023

Trends Sci

View full text Add to dashboard Cite

show abstract

“…Film cooling on a turbine blade leading edge was experimentally studied by Liu et al, 4 where two injection hole configurations were investigated: cylindrical holes and converged slot holes. Guelailia et al 5 numerically investigated the effects of mass flow rate on film cooling performance and heat transfer over a gas turbine rotor blade. Their results showed that converging slot holes provided better film cooling protection than simple cylindrical holes.…”

Section: Introductionmentioning

confidence: 99%

Effect of lid height and blowing ratio on film cooling effectiveness of a novel lidded hole configuration

Guelailia

Khorsi

Slimane

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part E:

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Film cooling is one of the promising technologies used for protecting rocket nozzles and turbine blades from combustion chamber hot gases. This paper proposes a novel shape of film cooling injection hole, called lidded hole, that can offer significant enhancement of cooling performance. ANSYS CFX is used to perform 3D numerical simulations of a flat plate with a single row of lidded holes, in which the k–ε model approximates turbulence effects. Four cases are investigated to highlight the influence of the hole's lid height (H/d = 0, 0.25, 0.5, 0.75). The effect of blowing ratios (M = 0.5, 1, 1.5) is also analyzed for each configuration. The numerical results of this study are compared with available experimental data, and, generally, a good agreement is achieved. The results obtained show that the lidded hole configuration reduces the coolant flow separation which improves significantly the film cooling effectiveness. In addition, increasing the blowing ratio leads to an increase in lateral and centerline cooling effectiveness. Comparing all studied cases, the optimum coolant coverage was obtained for the lidded hole configuration with H/d = 0.25 at M = 1.5.

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“…The purpose of this work has nothing to do with the suction of the boundary layer or the film cooling technics M.K Hamidou and al. [1]. So we take advantage of the expansion process through the converging spiral housing (volute) of the turbine from its subsonic inlet at zero azimuth angle located on the tongue to the lowest pressure at the volute exit located beneath the tongue in the vicinity of 355° azimuth angle, resulting in a strong pressure gradient between the upside and the downside of the tongue.…”

Section: Introductionmentioning

confidence: 99%

Performance investigation of a volute porous tongue of a turbocharger turbine

2020

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The design for better performance of the spiral housing volute used commonly in radial and mixed inflow gas turbines is of prime importance as it affects the machine stage at both design and off design conditions. The tongue of the scroll divides the flow into two streams, and represents a severe source of disturbances, in terms of thermodynamic parameter uniformity, maximum kinetic energy, the right angle of attack to the rotor and minimum losses. Besides, the volute suffers an undesirable effect due to the recirculating mass flow rate in near bottom vicinity of the tongue. The present project is an attempt to design a tongue fitted with cylindrical holes traversing normal to the stream wise direction, where on account of the large pressure difference between the top and the bottom sides of the tongue will force the recirculating flow to go through the rotor inlet. This possibility with its limitations has not yet been explored. A numerical simulation is performed which might provide our suitable objectives. To achieve this goal the ANSYS code is used to build the geometry, generate the mesh, and to simulate the flow by solving numerically the averaged Navier Stokes equations. Apparently, the numerical results show evidence of favorable impact in using porous tongue. The realization of a contact between the main and recirculation flow by drilled holes on the tongue surface leads to a flow field uniformity, a reduction in the magnitude of the loss coefficient, and a 20 % reduction in the recirculating mass flow rate.

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Computation of leading edge film cooling from a CONSOLE geometry (CONverging Slot hOLE)

Cited by 13 publications

References 22 publications

Effects of Crescent Shaped Block Width and Length on Flow Field and Film Cooling Performance

Effects of Crescent Shaped Block Width and Length on Flow Field and Film Cooling Performance

Effect of lid height and blowing ratio on film cooling effectiveness of a novel lidded hole configuration

Performance investigation of a volute porous tongue of a turbocharger turbine

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