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A Rapid Method for Calculating the “Off-Design” Performance of Compressors and Turbines

Published online by Cambridge University Press:  07 June 2016

J. H. Horlock
J. H. Horlock*
Affiliation:
University Engineering Laboratory, Cambridge*
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Summary

A model for the calculation of the “off-design” performance of turbo-machines has been suggested by Mellor, who proposed that the machine be split into an infinite number of stages, each producing a small change in stagnation enthalpy. This note suggests that the overall performance of a machine may be obtained in an integral form which permits a rapid calculation of performance maps for rotational speeds and flow rates not greatly different from design values. The method may be of use in preliminary design studies of multi-stage compressors and turbines.

Type
Research Article
Information
Aeronautical Quarterly , Volume 9 , Issue 4 , November 1958 , pp. 346 - 360
Copyright
Copyright © Royal Aeronautical Society. 1958

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References

1. Mellor, George L. Jr., The Aerodynamic Performance of Axial Compressor Cascades with Application to Machine Design. Sc.D. Thesis, Massachusetts Institute of Technology, February 1957.Google Scholar
2. Howell, A. R. and Bonham, R. P. Overall and Stage Characteristics of Axial Flow Compressors. Proceedings of the Institution of Mechanical Engineers, Vol. 163, p. 235, 1950.Google Scholar
3. Stodola, A. Steam and Gas Turbines. McGraw-Hill, New York, 1927. Reprinted by Smith, Peter, New York, 1945.Google Scholar