Experimental results are presented that describe the effects of embedded, longitudinal vortices on heat transfer and film injectant downstream of a single row of film cooling holes with compound angle orientations. Holes are spaced 7.8 hole diameters apart in the spanwise direction so that information is obtained on the interactions between the vortices and the injectant from a single hole. The compound angle holes are oriented so that their angles with respect to the test surface are 30 deg in a spanwise/normal plane projection, and 35 deg in a streamwise/normal plane projection. A blowing ratio of 0.5 is employed and the ratio of vortex core diameter to hole diameter is 1.6–1.67 just downstream of the injection holes (x/d=10.2). At the same location, vortex circulation magnitudes range from 0.15 m2/s to 0.18 m2/s. The most important conclusion is that local heat transfer and injectant distributions are strongly affected by the longitudinal embedded vortices, including their directions of rotation and their spanwise positions with respect to film injection holes. To obtain information on the latter, clockwise rotating vortices R0–R4 and counterclockwise rotating vortices L0–L4 are placed at different spanwise locations with respect to the central injection hole located on the spanwise centerline. With vortices R0–R4, the greatest disruption to the film is produced by the vortex whose downwash passes over the central hole (R0). With vortices L0–L4, the greatest disruption is produced by the vortices whose cores pass over the central hole (L1 and L2). To minimize such disruptions, vortex centers must pass at least 1.5 vortex core diameters away from an injection hole on the upwash sides of the vortices and 2.9 vortex core diameters away on the downwash sides of the vortices. Differences resulting from vortex rotation are due to secondary flow vectors, especially beneath vortex cores, which are in different directions with respect to the spanwise velocity components of injectant after it exits the holes. When secondary flow vectors near the wall are in the same direction as the spanwise components of the injectant velocity (vortices R0–R4), the film injectant is more readily swept beneath vortex cores and into vortex upwash regions than for the opposite situation in which near-wall secondary flow vectors are opposite to the spanwise components of the injectant velocity (vortices L0–L4). Consequently, higher Stanton numbers are generally present over larger portions of the test surface with vortices R0–R4 than with vortices L0–L4.
Skip Nav Destination
Article navigation
October 1994
Research Papers
Effects of Embedded Vortices on Injectant From Film Cooling Holes With Large Spanwise Spacing and Compound Angle Orientations in a Turbulent Boundary Layer
P. M. Ligrani,
P. M. Ligrani
Department of Mechanical Engineering, University of Utah, Salt Lake City, UT
Search for other works by this author on:
S. W. Mitchell
S. W. Mitchell
Department of Mechanical Engineering, Naval Postgraduate School, Monterey, CA
Search for other works by this author on:
P. M. Ligrani
Department of Mechanical Engineering, University of Utah, Salt Lake City, UT
S. W. Mitchell
Department of Mechanical Engineering, Naval Postgraduate School, Monterey, CA
J. Turbomach. Oct 1994, 116(4): 709-720 (12 pages)
Published Online: October 1, 1994
Article history
Received:
March 3, 1993
Online:
June 9, 2008
Article
Article discussed|
View article
Connected Content
A commentary has been published:
Closure to “Discussion of ‘Adiabatic Shear Localization in a Liquid Lubricant Under Pressure’” (1994, ASME J. Tribol., 116, p. 709)
Citation
Ligrani, P. M., and Mitchell, S. W. (October 1, 1994). "Effects of Embedded Vortices on Injectant From Film Cooling Holes With Large Spanwise Spacing and Compound Angle Orientations in a Turbulent Boundary Layer." ASME. J. Turbomach. October 1994; 116(4): 709–720. https://doi.org/10.1115/1.2929464
Download citation file:
Get Email Alerts
Related Articles
The Dynamics of the Horseshoe Vortex and Associated Endwall Heat Transfer—Part I: Temporal Behavior
J. Turbomach (October,2006)
Interactions Between Embedded Vortices and Injectant From Film Cooling Holes With Compound Angle Orientations in a Turbulent Boundary Layer
J. Turbomach (January,1994)
Boundary Layer Influence on the Unsteady Horseshoe Vortex Flow and Surface Heat Transfer
J. Turbomach (January,2009)
Improving Purge Air Cooling Effectiveness by Engineered End-Wall Surface Structures—Part I: Duct Flow
J. Turbomach (September,2018)
Related Proceedings Papers
Related Chapters
Pulsating Supercavities: Occurrence and Behavior
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Experimental and Numerical Investigation of Vortex Dynamics in Ventilated Cavitating Flows Around a Bluff Body
Proceedings of the 10th International Symposium on Cavitation (CAV2018)