Quantifying Blowing Ratio for Shaped Cooling Holes

[+] Author and Article Information
David Cerantola

Department of Mechanical and Materials Engineering, Queen's University, Kingston, ON, K7L 3N6, Canada

Michael Birk

Department of Mechanical and Materials Engineering, Queen's University, Kingston, ON, K7L 3N6, Canada

1Corresponding author.

ASME doi:10.1115/1.4038277 History: Received September 12, 2017; Revised October 22, 2017


Effusion cooling was a popular technology integrated into the design of gas turbine combustor liners. A staggering amount of research was completed that quantified performance with respect to operating conditions and cooling hole geometric properties; however, most of these investigations did not address the influence of the manufacturing process on the hole shape. This study completed an adiabatic wall numerical analysis using the realizable k-epsilon turbulence model of a laser-drilled hole that had a nozzled profile with an area ratio of 0.24 and five additional cylindrical, nozzled, diffusing, and filleted holes that yielded the same hole mass flow rate at representative engine conditions. The traditional methods for quantifying blowing ratio yielded the same value for all holes that was not useful considering the substantial differences in film cooling performance. It was proposed to define hole mass flux based on the outlet y-cross sectional area projected onto the inclination angle plane. This gave blowing ratios that correlated to better and worse cooling performance for the diffusing and nozzled holes respectively. The diffusing hole delivered the best film cooling due to having the lowest effluent velocity and greatest amount of in-hole turbulent production, which coincided with the worst discharge coefficient

Copyright (c) 2017 by ASME; use license CC-BY 4.0
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