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Calculation of Heat Transfer Coefficients in Cooled Turbine Cascades

Published online by Cambridge University Press:  07 June 2016

H. D. Harris  and
R. E. Luxton
H. D. Harris
Affiliation:
Department of Mechanical Engineering, University of Sydney
R. E. Luxton
Affiliation:
Department of Mechanical Engineering, University of Sydney
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Summary

An approximate method is presented for the calculation of heat transfer rates to cooled turbine blades. The method is based on a combination and extension of methods which have been developed in recent years for the calculation of the skin friction and heat transfer coefficients on wings in high speed flight. The use of the method is demonstrated by application to a specific cascade for which an experimental determination of overall heat transfer coefficient is known. Very close agreement with the experimental results is found over the range of Reynolds number tested. The calculated distribution of local heat transfer coefficient indicates that local pressure gradients have a marked effect on the heat transfer. A first-order estimate of the effect of blade cooling on the rate of mass flow through a blade passage shows that an increase of the order of one per cent in the mass flow rate may be obtained by a reasonable degree of blade cooling.

Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 3 , August 1966 , pp. 253 - 268
Copyright
Copyright © Royal Aeronautical Society. 1966

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References

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