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Application of Film Cooling Theory to the Cooling of Aircraft Gas Turbine Chambers

Published online by Cambridge University Press:  04 July 2016

G. J. Sturgess
G. J. Sturgess*
Affiliation:
University of Technology, Loughborough
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Extract

Film cooling performance expressed in the terms of film effectiveness, is divided into initial and final regions containing respectively, the potential core and transition lengths and, the main decay region. The theory of Kutateladze and Leont'ev, which is representative of present approaches, is presented and shown not to apply to the film initial region. To resolve the questions, what is the minimum acceptable value of effectiveness in a given situation, and, what proportion of the resulting maximum permissible cooled distance is initial region, the film cooling of a hypothetical turbojet engine to power a Mach 2-2 cruise supersonic air liner is examined. Experimental data from cooling devices representative of current European practice are used in the analysis to give realistic results.

Type
Research Article
Information
The Aeronautical Journal , Volume 71 , Issue 678 , June 1967 , pp. 430 - 434
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.Kutateladze, S. S. and Leont'ev, A. I.Film Cooling with a Turbulent Gaseous Boundary Layer. Academy of Sciences of USSR, Thermal Physics of High Temperatures, Vol 1, No 2, p 281, 1963.Google Scholar
2.Nishiwaki, N., Hirata, M. and Tsuchida, A.Heat Transfer on a Surface Covered by Cold Air Film. Paper presented at International Heat Transfer Conference, University of Colorado, 1961.Google Scholar
3.Hartnett, J. P., Birkebak, R. C. and Eckert, E. R. G.Velocity Distributions, Temperature Distributions, Effectiveness and Heat Transfer for Air Injected through a Tangential Slot into a Turbulent Boundary Layer. Trans ASME, Journal of Heat Transfer, p 293, Aug 1961.Google Scholar
4.Seban, R. A.Heat Transfer and Effectiveness for a Turbulent Boundary Layer with Tangential Fluid Injection. Trans ASME, Journal of Heat Transfer, p 303, Nov 1960.Google Scholar
5.Cole, E. H. and Peerless, S. J. Film Cooling in Incompressible Turbulent Flow: A Revised and Collective Presentation of the Data for the Adiabatic Wall Tempera ture Distribution. ARC 25, 310, Nov 1963.Google Scholar
6.Stollery, J. L. A Correlation of Some Experimental Data on the Length of the Potential Core Region. Imperial College Unpublished Report HRI/13, Dec 1963.Google Scholar
7.Lefebvre, A. H. and Herbert, M. V.Heat Transfer Processes in Gas Turbine Combustion Chambers. Proc Inst Mech Eng, Vol 174, No 12, p 463, 1960.Google Scholar
8.Spalding, D. B. A Relationship Between the Effectiveness and the Heat Transfer Coefficient in Film Cooling. Imperial College Unpublished Report IC/HRJ/20, Oct 1963.Google Scholar
9.Hartnett, J. P., Birkebak, R. C. and Eckert, E. R. G.Velocity Distributions, Temperature Distributions, Effectiveness and Heat Transfer in Cooling of a Surface with a Pressure Gradient. Paper presented at International Heat Transfer Conference, University of Colorado, 1961.Google Scholar
10.Sturgess, G. J.Comment on Prediction of Adiabatic Wall Temperatures in Film-cooling Systems. AIAA Journal. Vol 4, p 763, 1966.Google Scholar
11.Spalding, D. B.The Prediction of Adiabatic Wall Temperatures in Film Cooling Systems. AIAA Journal, Vol 3, p 965, 1965.Google Scholar