This paper discusses the mechanics of surge as observed on the high-speed axial compressors of modern aero-engines. It argues that the initial stage of the instability consists of a high-amplitude blast wave that develops nonlinearly from a small-scale disturbance and is thus not correctly described by traditional small perturbation stability theories. It follows from this that active control schemes of the global type may be inappropriate, since to be effective, control would have to be applied in a short time and in a very detailed manner, requiring a large number of transducers and actuators. Active control may, though, be effective in controlling the disturbances that grow into the above blast wave and in the control of other phenomena such as rotating stall, given an adequate number of transducers.
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April 1991
Research Papers
High-Speed Compressor Surge With Application to Active Control
A. M. Cargill,
A. M. Cargill
Rolls-Royce plc, Derby DE2 8BJ United Kingdom
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C. Freeman
C. Freeman
Rolls-Royce plc, Derby DE2 8BJ United Kingdom
Search for other works by this author on:
A. M. Cargill
Rolls-Royce plc, Derby DE2 8BJ United Kingdom
C. Freeman
Rolls-Royce plc, Derby DE2 8BJ United Kingdom
J. Turbomach. Apr 1991, 113(2): 303-311 (9 pages)
Published Online: April 1, 1991
Article history
Received:
February 15, 1990
Online:
June 9, 2008
Citation
Cargill, A. M., and Freeman, C. (April 1, 1991). "High-Speed Compressor Surge With Application to Active Control." ASME. J. Turbomach. April 1991; 113(2): 303–311. https://doi.org/10.1115/1.2929108
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