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TECHNICAL PAPERS

Transonic Aerodynamic Losses Due to Turbine Airfoil, Suction Surface Film Cooling

[+] Author and Article Information
D. J. Jackson, K. L. Lee, P. M. Ligrani

Convective Heat Transfer Laboratory, Department of Mechanical Engineering, University of Utah, Salt Lake City, UT 84112

P. D. Johnson

Turbines and Mechanical Components, Pratt & Whitney—Florida, United Technologies, Inc., West Palm Beach, FL 33410

J. Turbomach 122(2), 317-326 (Feb 01, 1999) (10 pages) doi:10.1115/1.555455 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

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Figures

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Schematic diagrams of: (a) the test section, and (b) the test airfoil
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Airfoil Mach number distribution
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Numerically computed Mach number distribution through the test section
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Schlieren images showing: (a) no trailing edge shock waves with no flow, and (b) a pair of oblique shock waves at the airfoil trailing edge. Flow moves from left to right in each image.
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Discharge coefficients, both with and without free-stream crossflow, as dependent upon coolant to free-stream pressure ratio for: (a) round cylindrical holes (RCH), and (b) conical diffused holes (CDH)
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Profiles measured one chord length downstream of the airfoil for “cold” film injection at ρc=1.0–1.2 from round cylindrical holes (RCH): (a) normalized local total pressure losses, (b) normalized Mach number, and (c) normalized kinetic energy.
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Profiles measured one chord length downstream of the airfoil for “cold” film injection at ρc=1.0–1.3 from conical diffused holes (CDH): (a) normalized local total pressure losses, (b) normalized Mach number, and (c) normalized kinetic energy
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Normalized total pressure losses in the free stream due to trailing edge, oblique shock waves as dependent upon blowing ratio for round cylindrical holes (RCH) and conical diffused holes (CDH)
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Comparison of integrated aerodynamic losses as dependent upon Mach number ratio from round cylindrical holes (RCH) and conical diffused holes (CDH), after correction for the presence of trailing edge oblique shock waves
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Comparison of integrated aerodynamic losses as dependent upon momentum flux ratio from round cylindrical holes (RCH) and conical diffused holes (CDH), after correction for the presence of trailing edge oblique shock waves
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Comparison of normalized integrated aerodynamic loses relative (minus integrated aerodynamic losses with no film cooling) at different blowing ratios (after correction for the presence of trailing edge oblique shock waves) with correlating Eq. (3)
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Film cooling hole geometries
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University of Utah Transonic Wind Tunnel (TWT) including film injection system

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