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International Journal of Rotating Machinery
Volume 2 (1996), Issue 4, Pages 259-267

Film Cooling from a Single Row of Compound Angle Holes at High Blowing Ratios

1Convective Heat Transfer Laboratory, Department of Mechanical Engineering, University of Utah, Salt Lake City 84112, Utah, USA
2Turbo and Power Machinery Research Center, Department of Mechanical Engineering, Seoul National University, Seoul 151-742, Korea

Copyright © 1996 Hindawi Publishing Corporation. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


Experimental results are presented which describe the development and structure of flow downstream of a single row of holes with compound angle orientations producing film cooling at high blowing ratios. This film cooling configuration is important because similar arrangements are frequently employed on the first stage of rotating blades of operating gas turbine engines. With this configuration, holes are spaced 6d apart in the spanwise direction, with inclination angles of 24 degrees, and angles of orientation of 50.5 degrees. Blowing ratios range from 1.5 to 4.0 and the ratio of injectant to freestream density is near 1.0. Results show that spanwise averaged adiabatic effectiveness, spanwise-averaged iso-energetic Stanton number ratios, surveys of streamwise mean velocity, and surveys of injectant distributions change by important amounts as the blowing ratio increases. This is due to injectant lift-off from the test surface just downstream of the holes.