Numerical Investigation on the Effects of the Deposit Height and Position on the Film Cooling Efficiency
A. Guelailia1,2, A. Khorsi2, S. A. Slimane1,2, M. M. Bencherif2,3, K. Gourssma2
1Centre of Satellite Development (CDS), Space Mechanical Research Department, BP 4065 Ibn Rochd USTO, Oran, Algeria
2Laboratory of Applied Mechanics, Faculty of Mechanical Engineering, University of Sciences and Technology Mohamed Boudiaf, BP 1505, El M'Nouar, 31001 Oran, Algeria
3Ecole Nationale Polytechnique d'Oran Maurice Audin, Route d'Es-Senia, B.P. 1523 El M'Naouer 31000, Oran, Algerie
Keywords: вычислительная гидродинамика, тепломассообмен, турбулентность, тепловая защита, сопло ракеты, пленочное охлаждение, отложение, computational fluid dynamics, heat and mass transfer, turbulence, thermal protection, rocket nozzle, film cooling, deposit
Abstract
The main objective of this study is to analyze the effect of the solid deposits downstream of the injection hole on the film cooling efficiency by highlighting the impact of several geometrical and physical parameters, such as the blowing ratio, deposit position, and deposit height, by using the ANSYS CFX software. Several configurations are tested by changing the deposit position and deposit height. The turbulence is approximated by the shear stress transport (SST) model. The film cooling effectiveness distributions are presented for different blowing ratios. The numerical results are compared with available experimental data, and good agreement is noted.
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