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Some Basic Studies of Liquid Propellant Injection Processes*

Published online by Cambridge University Press:  04 July 2016

J. D. Lewis
J. D. Lewis*
Affiliation:
Rocket Propulsion Establishment, Westcott
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Summary

The recent analytical studies of rocket engine combustion based on propellant vaporisation as the rate controlling parameter, especially those by Spalding, and Priem and Heidmann, have contributed greatly to our appreciation of the mechanism of stable combustion. Critical combustion experiments on a small scale engine have shown fair agreement with vaporisation predictions, but have also revealed the need to understand and improve the mixing process.

In parallel with performance measurements in a combustion system, detailed measurements of the atomisation process including the break-up mechanism and drop-size distribution have been made. However, there are many gaps in our knowledge of the subject and further work remains to be done.

It is thought that the high-speed photographic and gas sampling techniques developed for these investigations provide useful research tools for more detailed studies of the problems.

Type
Research Article
Information
The Aeronautical Journal , Volume 68 , Issue 647 , November 1964 , pp. 743 - 750
Copyright
Copyright © Royal Aeronautical Society 1964

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References

1.Spalding, D. B. A One-Dimensional Theory of Liquid-Fuel Rocket Combustion. A.R.C. 20175, May 1958.Google Scholar
2.Priem, R. J. and Heidmann, M. F. Propellent Vaporization as a Design Criterion for Rocket Engine Combustion Chambers. NASA Technical Report R-67, 1960.Google Scholar
3.Dell, H. A., Hobbs, D. S. and Richards, M. S. An Automatic Particle Counter and Sizer. Philips Tech. Rev., Vol. 21, No. 9, pp. 253-267, 1960.Google Scholar
4.Gardiner, J. A. Unpublished Work at N.G.T.E., Pyestock, 1961.Google Scholar
5.Heidmann, M. F. and Foster, H. H. Effect of Impingement Angle on Drop-Size Distribution and Spray Pattern of Two Impinging Jets. NASA Technical Note D-872, 1961.Google Scholar
6.Giffen, E. and Lamb, T. A. J. The Effect of Air Density on Spray Atomization. Motor Industry Res. Ass. Report No. 1953/5, 1953.Google Scholar
7.Krieg, H. C. and Coultas, G. A. Analytical and Experimental Stability Scaling Techniques. The Combustion Institute, W.S.S. Paper No. 61-12, 1961.Google Scholar
8.Osborn, J. R.Effect of Fuel Composition on High Frequency Oscillations in Rocket Motors Burning Premixed Hydrocarbon Gases and Air. Am. Rocket Soc. Jnl., Vol. 31, No. 10, pp. 1397–1401, 1961.Google Scholar
9.Lane, W. R.Shatter of Drops in Streams of Air. Ind. Eng. Chem., Vol. A3, p. 1312, 1951.CrossRefGoogle Scholar
10.Priem, R. J.Break-up of Water Drops and Sprays with a Shock Wave. Jet Propulsion, Vol. 27, 1084, 1957.CrossRefGoogle Scholar
11.Lewis, J. D. and Merrington, A. C.Combustion of n-Heptane Spray in the Decomposition Products of Concentrated Hydrogen Peroxide. Seventh Symposium (International) on Combustion, p. 953. Butterworths Scientific Publications, London, 1959.Google Scholar
12.Lewis, J. D. and Harrison, D.A Study of Combustion and Recombination Reactions During the Nozzle Expansion Process of a Liquid Propellant Rocket Engine. Eighth Symposium (International) on Combustion. Butterworths Scientific Publications, London, 1964. Google Scholar