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A Three-Dimensional Analysis of Rotor Wakes

Published online by Cambridge University Press:  07 June 2016

C E Whitfield ,
J C Kelly  and
B Barry
C E Whitfield
Affiliation:
Loughborough University of Technology
J C Kelly
Affiliation:
MTU, Munich
B Barry
Affiliation:
Rolls-Royce (1971) Ltd, Derby
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Summary

Many investigators have studied the aerodynamics of axial flow turbomachinery but none has produced a complete map of the three-dimensional flow behind a rotor row. This is of considerable interest to the aero-acoustician. A system is described which uses a constant temperature hot-wire anemometer to analyse the flow behind such a rotor. Although much information may be extracted by using the technique, its interpretation depends to a large extent on its form of presentation. An analysis of the flow behind a research fan is used as a means of discussing various forms of visual presentation.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 4 , November 1972 , pp. 285 - 300
Copyright
Copyright © Royal Aeronautical Society. 1972

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References

1. Ainley, D G Jeffs, R A Analysis of the air flow through four stages of half-vortex blading in an axial compressor. Power Jets Report 1199, April 1946.Google Scholar
2. Bowen, J T Sabersky, R H Rannie, W D Investigations of axial-flow compressors. American Society of Mechanical Engineers, Transactions, Vol 73, pp 1-15, 1951.Google Scholar
3. Dean, R C The influence of tip clearance on boundary-layer flow in a rectilinear cascade. Massachusetts Institute of Technology, Gas Turbine Laboratory Report 27-3, December 1954.Google Scholar
4. Fessier, T E Hartmann, M J Preliminary survey of compressor rotor-blade wakes and other flow phenomena with a hot-wire anemometer. NACA RM E56A13, 1956.Google Scholar
5. Gearhart, W S Tip clearance flow in turbomachines. Ordnance Research Laboratories, Pennsylvania State University Institute for Science and Engineering, Technical Memorandum N65-10918, AD451 200, August 1964.Google Scholar
6. Gregory-Smith, D G An investigation of annulus wall boundary layers in axial flow turbomachines. American Society of Mechanical Engineers, Paper 70-GT-92, 1970.Google Scholar
7. Herzig, H Z Hansen, A G Costello, G R A visualisation study of secondary flows in cascades. NACA Report 1163, 1954.Google Scholar
8. Horlock, J H The development of the outer wall annulus boundary layer in a compressor stage. ARC Report 18 392, 1955.Google Scholar
9. Horlock, J H Louis, J F Pereival, P M E Lakshminarayana, B Wall stall in compressor cascades. American Society of Mechanical Engineers, Paper 64-WA/FE-29, 1964.Google Scholar
10. Kerrebrock, J L Miko1ajczak, A A Intra-stator transport of rotor wakes and its effect on compressor performance. American Society of Mechanical Engineers, Paper 70-GT-39, 1970.Google Scholar
11. Klein, A Investigation of the effect of the entry boundary layer on the secondary flows in the blading of axial flow turbines. Forschung auf dem Gebiete des Ingenieurwesens, Vol 32, pp 175-187, 1966.Google Scholar
12. Lakshminarayana, B Horlock, J H Secondary flows and losses in cascades and axial flow turbomachines. International Journal of Mechanical Sciences, Vol 5, pp 287-307, 1963.Google Scholar
13. Lakshminarayana, B Horlock, J H Leakage and secondary flows in compressor cascades. ARC Report 26 821, 1967.Google Scholar
14. Lakshminarayana, B Horlock, J H Methods of predicting the tip clearance effects in axial flow turbomachinery. Journal of Basic Engineering, Vol 92, pp 467-482, September 1970.CrossRefGoogle Scholar
15; Lieblein, S Ackley, R H Secondary flows in annular cascades and effects on flows in inlet guide vanes. NACA RM E51G27, 1951.Google Scholar
16. Moore, R W Richardson, D L Skewed boundary layer flow near the end walls of a compressor cascade. American Society of Mechanical Engineers, Transactions, Vol 79, pp 1789-1800, 1957.Google Scholar
17. Otsuka, S Sugiyama, Y On the performance of a wing having tip clearance. I: The case in which the tip clearance is contained within a non-uniform flow. Nagoya University Faculty of Engineering Memoirs, Vol 21, pp 172-188, May 1969.Google Scholar
18. Rains, D A Tip clearance flows in axial flow compressors and pumps. California Institute of Technology, Hydrodynamics and Mechanical Engineering Laboratories, Report 5, June 1954.Google Scholar
19. Rohlik, H E Kofskey, M G Allen, H W Herzig, H Z Secondary flows and boundary layer accumulations in turbine nozzles. NACA Report 1168, 1954.Google Scholar
20. Toyokura, T Kubota, N Studies on back-flow mechanism of turbomachines. I: Back-flow mechanism to the suction side of axial-flow impeller blades. Japan Society of Mechanical Engineers Bulletin, Vol 11, pp 147-156, February 1968.Google Scholar
21. Ufer, H Analysis of velocity distributions near the tips of axial flow fan blades. Technische Mitteilungen Krupp Forschungsbericht, Vol 26, pp 33-45, 1968.Google Scholar
22. Weske, J R An investigation of the aerodynamic characteristics of a rotating axial flow blade grid. NACATN 1128, 1947.Google Scholar
23. Williams, A D The effect of tip clearance flows on performance of axial flow compressors. California Institute of Technology, Aeronautical Engineering Thesis, 1960.Google Scholar