A Comparative Study of the Film Cooling Hole Configuration Effects on the Leading Edge of Asymmetrical Turbine Blade
Year: 2009
Type: conference-paper
Abstract: \n The focus of this comparative-numerical study is to investigate the effects of advanced\n cooling hole geometries on film cooling effectiveness. Computational results are presented\n for a row of coolant injection holes on each side of an asymmetrical turbine blade model\n near the leading edge. Six film cooling configurations are considered in the present\n study, namely: (1) a cylindrical film hole, (2) a shaped film hole, (3) a uniform film\n slot, (4) a convergent film slot, (5) a crescent film hole, and (6) a trenched film hole.\n All simulations are conducted for the same density ratio of 1.0 and the same inlet plenum\n pressure. A new parameter, Rc, is defined to measure the rate of blade\n coverage by the film cooling. Results show that, at the suction side, except for the\n trenched case, all configurations provide an increase of film effectiveness, specially the\n crescent slot case which provides the highest increase over the baseline case. On pressure\n side, the five configurations produce better quality of cooling and an enhancement which\n reaches 60% for the crescent hole case. The best blade coverage by the film cooling is\n allotted to the two cases: uniform and converge slot configurations.\n
Authors: Mustapha Benabed, Abbes Azzi, B. A. Jubran
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W1997086993