Oil-film flow visualizations and three-dimensional flow measurements using a five-hole probe have been conducted to investigate the flow characteristics and aerodynamic loss distributions of film-cooling jets with compound angle orientations. For a fixed inclination angle of the injection hole, measurements are performed at various orientation angles to the direction of the mainstream in the case of three velocity ratios of 0.5, 1.0, and 2.0. Flow visualizations for the velocity ratio of 2.0 show that the increase in the orientation angle furnishes better film coverage on the test surface, but gives rise to large flow disturbances in the mainstream. A near-wall flow model has been proposed based on the surface flow visualizations. It has also been found from the flow measurements that as the orientation angle increases, a pair of count-errotating vortices turn to a single strong one, and the aerodynamic loss field is closely related to the secondary flow. Even in the case of the velocity ratio of 2.0, aerodynamic loss is produced within the jet region when the orientation angle is large. Regardless of the velocity ratio, the mass-averaged aerodynamic loss increases with increasing orientation angle, the effect of which on aerodynamic loss is pronounced when the velocity ratio is large.
Skip Nav Destination
Article navigation
April 1997
Research Papers
Flow Characteristics and Aerodynamic Losses of Film-Cooling Jets With Compound Angle Orientations
Sang Woo Lee,
Sang Woo Lee
Department of Mechanical Engineering, Kum-Oh National University of Technology, Kumi, Kyungbook, Republic of Korea
Search for other works by this author on:
Yong Beom Kim,
Yong Beom Kim
Department of Mechanical Engineering, Kum-Oh National University of Technology, Kumi, Kyungbook, Republic of Korea
Search for other works by this author on:
Joon Sik Lee
Joon Sik Lee
Department of Mechanical Engineering, Seoul National University, Seoul, Republic of Korea
Search for other works by this author on:
Sang Woo Lee
Department of Mechanical Engineering, Kum-Oh National University of Technology, Kumi, Kyungbook, Republic of Korea
Yong Beom Kim
Department of Mechanical Engineering, Kum-Oh National University of Technology, Kumi, Kyungbook, Republic of Korea
Joon Sik Lee
Department of Mechanical Engineering, Seoul National University, Seoul, Republic of Korea
J. Turbomach. Apr 1997, 119(2): 310-319 (10 pages)
Published Online: April 1, 1997
Article history
Received:
February 27, 1995
Online:
January 29, 2008
Citation
Lee, S. W., Kim, Y. B., and Lee, J. S. (April 1, 1997). "Flow Characteristics and Aerodynamic Losses of Film-Cooling Jets With Compound Angle Orientations." ASME. J. Turbomach. April 1997; 119(2): 310–319. https://doi.org/10.1115/1.2841114
Download citation file:
Get Email Alerts
Related Articles
Secondary Flow Measurements in a Turbine Passage With Endwall Flow Modification
J. Turbomach (October,2000)
Effects of Swirl Velocities From Fan Assemblies Mounted on Lifting Surfaces
J. Eng. Gas Turbines Power (March,2011)
The Aerodynamic Mixing Effect of Discrete Cooling Jets With Mainstream Flow on a Highly Loaded Turbine Blade
J. Turbomach (July,1996)
Film-Cooling Flowfields With Trenched Holes on an Endwall
J. Turbomach (October,2009)
Related Proceedings Papers
Related Chapters
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression Systems: A Practical Approach, Second Edition
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression System: A Practical Approach, Third Edition
A Computational Assessment of Gas Jets in a Bubbly Co-Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)