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TECHNICAL PAPERS

Time-Resolved Vane-Rotor Interaction in a High-Pressure Turbine Stage

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

Whittle Laboratory, University of Cambridge, Cambridge, U.K. CB3 0DY

R. W. Moss

Department of Marine Technology, University of Newcastle, U.K.

R. W. Ainsworth

Department of Engineering Science, University of Oxford, Oxford, U.K. OX1 3PJ

C. K. Horwood

Rolls Royce plc., Derby, U.K. DE2 8BJ

J. Turbomach 125(1), 1-13 (Jan 23, 2003) (13 pages) doi:10.1115/1.1492823 History: Received June 20, 2000; Revised May 16, 2002; Online January 23, 2003
Copyright © 2003 by ASME
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References

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Figures

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(a) Schematic of two-dimensional vane rotor interaction, (b) schematic of the dominant rotor exit flow phenomena
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Schematic of the turbine stage in the Oxford Rotor Facility
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Fast-response pyramid probe
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Time-resolved total pressure measurements presented on both phase-time and phase-phase diagrams (measurements made along a circumferential arc close to the hub wall downstream of the HP stage)
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Expected structure of the exit flow from the HP stage (displayed as a phase-phase interaction diagram)
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Rotor exit Mach number measurements showing dominant structure of the flow (time-snapshot)
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Phase-phase interaction diagram—relative Mach number (height 2 is closest to the tip and height 19 is closest to the hub)
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Phase-phase interaction diagram—relative total pressure (height 2 is closest to the tip and height 19 is closest to the hub)
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Phase-phase interaction diagram—static pressure (height 2 is closest to the tip and height 19 is closest to the hub)
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The maximum and minimum (over a vane passing period) mean rotor exit isentropic Mach number (the line at Mach 0.98 signifies the approximate Mach number at which the rotor trailing edge shock forms)
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Linear cascade schlieren photograph (isentropic exit Mach no.=0.96)
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Linear cascade schlieren photograph (isentropic exit Mach no.=1.1)
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Numerical predictions of entropy migration (a), and vorticity development (b) through a rotor passage (no upstream vanes present)—(a) four slices on entropy; (b) two slices of stream-wise vorticity
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Numerical prediction of the total pressure and secondary flow vectors downstream of the rotor
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Numerical prediction of the time-resolved behavior of the trailing edge penetration depth of the suction surface separation line
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Variation of width and phase of the rotor wake with HP vane phase (rotor midheight experimental measurements)
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Comparison of HP stage and linear cascade exit traverses (16% vane phase Fig. 16)
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Comparison of HP stage and linear cascade exit traverses (40% vane phase Fig. 16)
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Time-resolved rotor exit diagram—relative total pressure (H1–H4 show line plots at four radial heights as the upstream vane moves through one vane pitch
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Time-resolved rotor exit diagram—relative Mach no. (H1-H4 show line plots at four radial heights as the upstream vane moves through one vane pitch

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