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Note on Matching a Supersonic Intake to an Aircraft Gas Turbine

Published online by Cambridge University Press:  04 July 2016

J. M. Stephenson
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Extract

The Function of the air intake of a gas turbine engine is to deliver whatever air mass flow is required, with the best recovery of ram stagnation pressure, over the desired range of flight speeds and altitudes.

Although it is generally shown in other forms, the performance of an air intake for supersonic flight can be represented on charts very similar to those of a rotating compressor. In Fig. 1 the ratio between ambient (static) pressure and stagnation pressure at the diffuser of a typical intake is shown as a function of corrected inlet and outlet air mass flow (which are themselves functions of the local flow Mach numbers), for a series of flight Mach numbers.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 62 , Issue 567 , March 1958 , pp. 219 - 220
Copyright
Copyright © Royal Aeronautical Society 1958

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References

1.Stephenson, J. M. (1952). A Solution of the Surging Problem in Axial-Flow Compressors. Journal of the Aeronautical Sciences pp. 67–69, January 1952.Google Scholar
2. British Patent 644, 955; Canadian Patent 500,962; U.S. Patent 2,709,036.Google Scholar
3.Wilcox, C. E. and Trout, A. M. (1951). Thrust Augmentation of Turbo-jet Engines by Water Injection at the Compressor Inlet. N.A.C.A. Report 1006, 1951.Google Scholar