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ADIABATIC FILM COOLING EFFECTIVENESS MEASUREMENTS THROUGHOUT MULTI-ROW FILM COOLING ARRAYS

[+] Author and Article Information
Greg Natsui

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

Zachary Little

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

Jayanta S. Kapat

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

Jason E. Dees

GE Global Research Niskayuna, NY, USA
deesj@ge.com

1Corresponding author.

ASME doi:10.1115/1.4035520 History: Received September 20, 2016; Revised November 07, 2016

Abstract

Adiabatic film cooling effectiveness measurements are obtained using pressure-sensitive paint (PSP) on a flat film cooled surface. The effects of blowing ratio and hole spacing are investigated for four multi-row arrays comprised of 8 rows containing 52 holes of 3.8 mm diameter with 20º inclination angles and hole length-to-diameter ratio of 11.2. The four arrays investigated have two different hole-to-hole spacings composed of cylindrical and diffuser holes. For the first case, lateral and streamwise pitches are 7.5 times the diameter. For the second case, pitch-to-diameter ratio is 14 in lateral direction and 10 in the streamwise direction. The holes are in a staggered arrangement. Adiabatic effectiveness measurements are taken for a blowing ratio range of 0.3 to 1.2 and a density ratio of 1.5, with CO2 injected as the coolant. Local effectiveness, laterally averaged effectiveness, boundary layer thickness, momentum thickness, turbulence intensity and turbulence length scale are presented. For the cylindrical holes, at the first row of injection, the film jets are still attached at a blowing ratio of 0.3. By a blowing ratio of 0.5, the jet is observed to lift off, and then impinge back onto the test surface. At a blowing ratio of 1.2, the jets lift off, but reattach much further downstream, spreading the coolant further along the test surface.

Copyright (c) 2016 by ASME
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