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Computational Thermal Sciences: An International Journal
ESCI SJR: 0.244 SNIP: 0.434 CiteScore™: 0.7

ISSN Imprimer: 1940-2503
ISSN En ligne: 1940-2554

Computational Thermal Sciences: An International Journal

DOI: 10.1615/ComputThermalScien.2017019230
pages 183-193

INFLUENCE OF LATERAL ANGLE ON FILM COOLING PERFORMANCE OVER ASYMMETRICAL TURBINE BLADE

Mustapha Benabed
Aeronautical Laboratory and Propulsive Systems, Faculte de Genie-Mecanique, Universite des Sciences et de la Technologie d'Oran, B.P. 1505 El-Mnouar, Oran, Algeria

RÉSUMÉ

A numerical investigation was performed to determine the effect of the lateral angle injection on film cooling effectiveness over a turbine blade. The rows are located in the vicinity of the stagnation line. One row is located on the suction side and the other one is on the pressure side. The predicted pressure field for various blowing ratios (M = 0.5, 1.1, and 1.5) is compared to available experimental results at the design condition. Moreover, the effect of three lateral angles 30, 45, and 60 deg at three blowing rates is investigated by analyzing the results of both laterally averaged and area-averaged values of adiabatic film cooling effectiveness. The outcomes of the numerical results indicate that the thermal protection of the blade can be strongly influenced by the lateral angle. The coolant structure flow is characterized by a dominant single asymmetric vortex on both sides. Lateral injection at angle γ = 60 deg significantly improves film cooling effectiveness. From γ = 30 to 45 deg, overall, no appreciable improvement could be noted in cooling performance except for the lower blowing ratio M = 0.5. At suction side, the increase of blowing ratio has an adverse effect on the blade thermal protection.


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