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Aerodynamic Performance of Porous Gas Turbine Blades

Published online by Cambridge University Press:  04 July 2016

F. J. Bayley  and
G. R. Wood
F. J. Bayley
Affiliation:
University of Sussex
G. R. Wood
Affiliation:
C. A. Parsons & Co Ltd, Newcastle-upon-Tyne Formerly of University of Sussex
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Extract

If maximum gas temperatures aire to rise appreciably above 1500°K, the value currently achieved in advanced aero-engines, alternatives to the present internal convective methods of air-cooling the first-stage turbine blades will have to be sought. One of the most promising developments lies in the use of porous blade materials, through which cooling air can be “effused” or “transpired”. In a recent paper Bayley and Turner have shown that by the combination of high heat transfer coefficients within the interstices of the porous material, and a reduction in heat transfer rate by injection into the boundary layer on the hot-gas side of the blade, effective cooling rates can be achieved.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 73 , Issue 705 , September 1969 , pp. 789 - 796
Copyright
Copyright © Royal Aeronautical Society 1969 

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References

1. Bayley, F. J. and Turner, A. B. The Heat Transfer Per formance of Porous Gas Turbine Blades. Aeronautical Journal of the Royal Aeronautical Society, Vol 72, No 696, pp 1087–1094, December 1968.Google Scholar
2. Dean, R. C. Aerodynamic Measurements. MIT Gas Turbine Lab, 1953.Google Scholar
3. Stringer, A. J. Unpublished Work. Mechanical Engineering Laboratories, University of Sussex.Google Scholar
4. Andrews, S. J. and Schofield, N. W. An Experimental Investigationn of a Thick-Aerofoil Nozzle Cascade. ARC, R and M 2883, 1950.Google Scholar
5. Kutateladze, S. S. and Leont'ev, A. I. Turbulent Boundary Layers in Compressible Gases. Arnold, London, 1964.Google Scholar
6. Spalding, D. B. and Cm, S. W. The Drag of a Compressible Turbulent Boundary Layer. Journal of Fluid Mechanics, Vol 18, 1964.Google Scholar
7. Wooldridge, C. E. and Muzzy, R. J. Boundary Layer Turbulence Measurement. AlAA Journal, Vol 4, No 11, 1966.Google Scholar
8. Ainley, D. G. Internal Air-Cooling for Turbine Blades. ARC. Rand M 3013,1957.Google Scholar
9. Ainley, D. G. and Mathieson, G. C. R. An Examination of the Flow and Pressure Losses in Blade Rows of Axial-Flow Turbines. ARC, R and M 2891, 1951.Google Scholar