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TECHNICAL PAPERS

Wake, Shock, and Potential Field Interactions in a 1.5 Stage Turbine—Part II: Vane-Vane Interaction and Discussion of Results

[+] Author and Article Information
R. J. Miller

Whittle Laboratory, University of Cambridge, Cambridge CD30DY, UK

R. W. Moss

Department of Marine Technology, University of Newcastle, Newcastle upon Tyne NE1 7RU, UK

R. W. Ainsworth

Department of Engineering Science, University of Oxford, Oxford OX13PJ, UK

N. W. Harvey

Rolls Royce plc. Derby DE24 8BJ, UK

J. Turbomach 125(1), 40-47 (Jan 23, 2003) (8 pages) doi:10.1115/1.1508387 History: Received January 31, 2002; Online January 23, 2003
Copyright © 2003 by ASME
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References

Miller,  R. J., Moss,  R. W., Ainsworth,  R. W., and Harvey,  N. W., 2002, “Wake, Shock and Potential Field Interactions in a 1.5 Stage Turbine—Part I: Vane-Rotor and Rotor-Vane Interaction,” ASME 2002-GT-30435, ASME J. Turbomach., 124, pp. 33–39.
Korakianitis,  T., 1993, “On the Propagation of Viscous Wakes and Potential Flow in Axial Turbine Cascades,” ASME J. Turbomach., 115, pp. 115–127.
Denton, J. D., 1990, “The Calculation of Three-Dimensional Viscous Flow Through Multistage Turbomachines,” ASME 90-GT-19.
Oppenheim, A. V., Willsky, A. S., and Withian, T. Y. 1983, Signals and Systems. Prentice Hall International Editions.
Mee,  D. J., Baines,  N. C., Oldfield,  M. L. G., and Dickens,  T. E., 1992, “An Examination of the Contributions to Loss on a Transonic Turbine Blade in a Cascade,” ASME J. Turbomach., 114 .
Giles,  M. B., 1990, “Stator-Rotor Interaction in a Transonic Turbine,” J. Propul. Power, 6 (5).

Figures

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Computational prediction of pressure on late suction surface (1st two harmonics of downstream vane passing frequency)
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Experimental measurement of the pressure on the late suction surface (ensemble averaged at downstream vane passing frequency)
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Deterministic component of pressure measurements made using sensor 11 at both upstream and downstream passing frequencies
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Blade surface isentropic Mach number distribution 5
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(a) Location of key surface pressure sensors; (b) rotor relative Mach number (Mach 1 line highlighted)
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Computational prediction of the square root of the power spectrum (suction surface)
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Suction surface sensor 11 (expanded)
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Suction surface sensor 8 (expanded)
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Suction surface sensor 7 (expanded)
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Suction surface pressure sensor 2
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Power spectrum created by idealized interaction between upstream and downstream vane
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Power spectrum calculated using measurements from suction surface sensor 11
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Schematic showing the structure of the unsteady flow field

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