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 multirow arrays comprised of eight rows containing 52 holes of 3.8 mm diameter with 20 deg 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 0.3–1.2 and a density ratio of 1.5, with CO2 injected as the coolant. A thorough boundary layer analysis is presented, and data were taken using hotwire anemometry with air injection, with boundary layer, and turbulence measurements taken at multiple locations in order to characterize the boundary layer. 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. A thorough uncertainty analysis has been conducted in order to fully understand the presented measurements and any shortcomings of the measurement technique. The maximum uncertainty of effectiveness and blowing ratio is 0.02 counts of effectiveness and 3%, respectively.
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October 2017
Research-Article
Adiabatic Film Cooling Effectiveness Measurements Throughout Multirow Film Cooling Arrays
Greg Natsui,
Greg Natsui
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: gnatsui@knights.ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: gnatsui@knights.ucf.edu
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Zachary Little,
Zachary Little
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Zachary.Little@ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Zachary.Little@ucf.edu
Search for other works by this author on:
Jayanta S. Kapat,
Jayanta S. Kapat
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Jayanta.Kapat@ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Jayanta.Kapat@ucf.edu
Search for other works by this author on:
Jason E. Dees
Jason E. Dees
Search for other works by this author on:
Greg Natsui
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: gnatsui@knights.ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: gnatsui@knights.ucf.edu
Zachary Little
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Zachary.Little@ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Zachary.Little@ucf.edu
Jayanta S. Kapat
Center for Advanced Turbomachinery
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Jayanta.Kapat@ucf.edu
and Energy Research,
Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
University of Central Florida,
Orlando, FL 32816
e-mail: Jayanta.Kapat@ucf.edu
Jason E. Dees
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 20, 2016; final manuscript received November 7, 2016; published online May 16, 2017. Editor: Kenneth Hall.
J. Turbomach. Oct 2017, 139(10): 101008 (12 pages)
Published Online: May 16, 2017
Article history
Received:
September 20, 2016
Revised:
November 7, 2016
Citation
Natsui, G., Little, Z., Kapat, J. S., and Dees, J. E. (May 16, 2017). "Adiabatic Film Cooling Effectiveness Measurements Throughout Multirow Film Cooling Arrays." ASME. J. Turbomach. October 2017; 139(10): 101008. https://doi.org/10.1115/1.4035520
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