Hostname: page-component-586b7cd67f-t7fkt Total loading time: 0 Render date: 2024-11-24T15:37:41.133Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access

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.

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

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

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