Heat and Mass Transfer Research Journal (HMTRJ)

Research Article

Numerical Investigation of Micro Hole Film Cooling Performance

Sana Abd Alsalam and Bassam Jubran

Aero-Thermal Management Laboratory, Department of Aerospace Engineering, Ryerson University, 350 Victoria St., Toronto, Ontario, Canada, M5B2K3.

Submitted: May 23, 2019; Revised August 22, 2019; Accepted: August 24, 2019

Abstract

Micro hole film cooling is an air-cooling technology and a new approach to improve the cooling performance and the thermal protection of turbine blades. This paper is a numerical study focuses on the effect of the blowing ratio and the freestream turbulence intensity on film cooling performance of a single round micro cooling hole with a 200 µm diameter on a flat plate model. The computation is performed on FLUENT-ANSYS to predict the film cooling effectiveness performance as well as the thermal and flow fields at various blowing ratios. The main findings of the analysis are that (1) the optimal cooling performance is attained at low blowing ratios, (2) in contrast to the cylindrical macro hole, the circular micro hole showed about 30 % increase in the averaged overall film cooling performance with approximately a 12 % reduction in the coolant blowing ratio at the highest averaged lateral film cooling effectiveness, (3) high freestream turbulence intensity causes an increase in the lateral average film cooling effectiveness while it has a minor effect on minimizing the centerline effectiveness.

Keywords

Film cooling, Micro hole film cooling, Film cooling effectiveness, Numerical simulation.

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