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The application of high pressure ejectors to reaction control systems

Published online by Cambridge University Press:  04 July 2016

P. Miller and
M. W. R. Seel
P. Miller
Affiliation:
School of Mechanical Engineering, University of Bath
M. W. R. Seel
Affiliation:
School of Mechanical Engineering, University of Bath
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Summary

A study of the thrust augmentation arising from the application of ejectors to high pressure reaction control systems typical of VSTOL aircraft is presented. A numerical analysis was undertaken to identify parameters critical to the attainment of high performance. A novel technique for improving mixing in confined ejector flows was investigated experimentally.

Theoretical work considered configurations with both sonic and supersonic primary flows. The studies show that thrust augmentation ratios ⋍ 1·3 are possible at pressure ratios around 15 using an ejector area ratio of 35. Little benefit accrues from diffusion at high pressure and performance is sensitive to mixing efficiency in terms of the mixing duct exit flow uniformity and primary nozzle losses.

Jets issuing from underexpanded nozzles fitted with castellations around their exit were compared experimentally with those leaving plain nozzles. Significant improvements in jet entrainment rates arise from the castellations. Strong correlation is observed between the free jet mixing rate and ejector secondary thrust. The level of thrust augmentation is low in conventional terms but constitutes a significant improvement over plain nozzle ejectors and non-augmented convergent nozzles.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 949 , November 1991, pp. 297 - 312
Copyright
Copyright © Royal Aeronautical Society 1991 

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Footnotes

*

Consultant. Part-time Research Officer, University of Bath.

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