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Computational Thermal Sciences: An International Journal
ESCI SJR: 0.249 SNIP: 0.434 CiteScore™: 0.7

ISSN Imprimir: 1940-2503
ISSN On-line: 1940-2554

Computational Thermal Sciences: An International Journal

DOI: 10.1615/ComputThermalScien.2016017410
pages 429-443

A NUMERICAL INVESTIGATION OF NEW FILM COOLING HOLE CONFIGURATION AT THE LEADING EDGE OF ASYMMETRICAL TURBINE BLADE: PART B

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

RESUMO

The focus of the second part of this numerical study is, firstly, to investigate the effects of the third new configuration, the slot with cylindrical hole midway (SWC), generated from two previous configurations, developed in Part A, by the combination between two film cooling configurations: cylindrical hole and uniform slot and secondly, to establish a final comparison between the three configurations. Computational results are presented for a row of coolant injection holes in each side of an asymmetrical turbine blade model near the leading edge. For each configuration, three values of the radius are taken: R = 0.4, R = 0.8, and R = 1.2. All simulations are conducted for the same density ratio of 1.0 and the same inlet plenum pressure. The new parameter, Rc, is defined to measure the ratio of blade coverage by the film cooling. The best cooling performances are allotted to the configurations with the smallest hole (cases 1, 4, and 7).


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