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research-article

GT2018-76964 Flow Statistics and Visualization of Multi-Row Film Cooling Boundary Layers Emanating from Cylindrical and Diffuser Shaped Holes

[+] Author and Article Information
Justin Hodges

Center for Advanced Turbomachinery and Energy Research, Laboratory for Turbine Aerodynamics, Heat Transfer and Durability, University of Central Florida, Orlando, FL, USA
Justin.Hodges@ucf.edu

Craig Fernandes

Center for Advanced Turbomachinery and Energy Research, Laboratory for Turbine Aerodynamics, Heat Transfer and Durability, University of Central Florida, Orlando, FL, USA
Fernandes.Craig@knights.ucf.edu

Erik Fernandez

Center for Advanced Turbomachinery and Energy Research, Laboratory for Turbine Aerodynamics, Heat Transfer and Durability, University of Central Florida, Orlando, FL, USA
Erik.Fernandez@ucf.edu

Jayanta Kapat

Center for Advanced Turbomachinery and Energy Research, Laboratory for Turbine Aerodynamics, Heat Transfer and Durability, University of Central Florida, Orlando, FL, USA
Jayanta.Kapat@ucf.edu

1Corresponding author.

ASME doi:10.1115/1.4041867 History: Received October 06, 2018; Revised October 23, 2018

Abstract

The research presented in this paper strives to exploit the benefits of near-wall measurement capabilities using hotwire anemometry and flowfield measurement capabilities using particle image velocimetry (PIV) for analysis of the injection of a staggered array of film cooling jets into a turbulent cross-flow. It also serves to give insight into the turbulence generation, jet structure, and flow physics pertaining to film cooling for various flow conditions. Such information and analysis will be applied to both cylindrical and diffuser shaped holes, to further understand the impacts manifesting from hole geometry. Spatially-resolved PIV measurements were taken at the array centerline of the holes and detailed temporally resolved hotwire velocity and turbulence measurements were taken at the trailing edge of each row of jets in the array centerline corresponding to the PIV measurement plane. Flowfields of jets emanating from eight staggered rows, of both cylindrical and diffuser shaped holes inclined at 20 degrees to the main-flow, are studied over blowing ratios in the range of 0.3-1.5. To allow for deeper interpretation, companion local adiabatic film cooling effectiveness results will also be presented for the geometric test specimen from related in-house work.

Copyright (c) 2018 by ASME
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