Experiments have been performed on the film cooling of gas turbine blades in order to study the influence of large temperature differences on the effectiveness of film cooling. A two-dimensional flat plate model was tested in a stream of 1000 K combustion gases flowing at between 110 and 170 m/s. The model was cooled on both sides by jets of air coming from flush angled slots. The range of velocity ratios Uc/Ug covered was from 0.3 to 1.7 and the range of blowing rates was between 0.5 and 5. Film cooling effectiveness was measured and boundary layer traverses were performed. It has been found that once radiation and conduction effects are taken into account, the simple equations proposed by previous workers for the constant property case could be used with little error.
Skip Nav Destination
Article navigation
January 1977
This article was originally published in
Journal of Engineering for Power
Research Papers
Film Cooling of Gas Turbine Blades: A Study of the Effect of Large Temperature Differences on Film Cooling Effectiveness
M. A. Paradis
M. A. Paradis
Department of Mechanical Engineering, Laval University, Quebec, P.Q., Canada
Search for other works by this author on:
M. A. Paradis
Department of Mechanical Engineering, Laval University, Quebec, P.Q., Canada
J. Eng. Power. Jan 1977, 99(1): 11-20 (10 pages)
Published Online: January 1, 1977
Article history
Received:
November 14, 1975
Online:
July 14, 2010
Citation
Paradis, M. A. (January 1, 1977). "Film Cooling of Gas Turbine Blades: A Study of the Effect of Large Temperature Differences on Film Cooling Effectiveness." ASME. J. Eng. Power. January 1977; 99(1): 11–20. https://doi.org/10.1115/1.3446240
Download citation file:
Get Email Alerts
Cited By
Experimental Characterization of Superheated Ammonia Spray From a Single-Hole Spray M Injector
J. Eng. Gas Turbines Power (August 2025)
Related Articles
Prediction of Film Cooling by a Row of Holes With a Two-Dimensional Boundary-Layer Procedure
J. Turbomach (October,1987)
The Effect of Internal Crossflow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes
J. Turbomach (July,2015)
A Detailed Analysis of Film Cooling Physics: Part III— Streamwise Injection With Shaped Holes
J. Turbomach (January,2000)
Double-Jet Ejection of Cooling Air for Improved Film Cooling
J. Turbomach (October,2007)
Related Chapters
Radiation
Thermal Management of Microelectronic Equipment
Radiation
Thermal Management of Microelectronic Equipment, Second Edition
How to Use this Book
Thermal Spreading and Contact Resistance: Fundamentals and Applications