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TECHNICAL PAPERS

Blade Row Interaction in a High-Pressure Steam Turbine

[+] Author and Article Information
V. S. P. Chaluvadi, A. I. Kalfas, H. P. Hodson

Whittle Laboratory, Cambridge University Engineering Department, Cambridge CB3 0DY, England

H. Ohyama, E. Watanabe

Turbine Engineering Department, Mitsubishi Heavy Industries, Takasago Machinery Works, Takasago Hyogo 676, Japan

J. Turbomach 125(1), 14-24 (Jan 23, 2003) (11 pages) doi:10.1115/1.1518504 History: Received December 12, 2002; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Schematic diagram of the test configuration
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Comparison of stagnation pressure loss coefficient (Y) at stator trailing edge (plane 1)—(a) measurements (b) steady CFD
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Comparison of spanwise variations of pitchwise averaged flow field at stator trailing edge (plane 1)—(a) absolute yaw angle, (b) stagnation pressure loss coefficient (Y)
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Comparison of rotor surface static pressure coefficient distributions (Cp)
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Comparison of relative stagnation pressure loss coefficient at rotor trailing edge (plane 2)—(a) measurements; (b) steady CFD, no shroud leakage; (c) steady CFD, with shroud leakage; (d) time average unsteady CFD, no shroud leakage
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Absolute velocity at rotor trailing edge measured with a SSHW at rotor midspan—(a) absolute velocity in rotor pitch, stator pitch plane; (b) velocity profile across section A-A; (c) velocity profile across section B-B
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Secondary flow lines at rotor trailing edge (plane 2) in relative frame of reference over one stator pitch
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Turbulence intensity contours at 10% Cx downstream of rotor trailing edge over one stator wake-passing period
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Comparison of the pitch-wise averaged unsteady flow field between the five-hole probe measurements and unsteady CFD at rotor trailing edge—(a) relative yaw angle, (b) stagnation pressure loss coefficient
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Loss generation rate in various regions of the blade row
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Logarithm of the entropy generation rate per unit volume (J/s K m3 ) in the rotor blade row from unsteady simulations—(a) at rotor midspan, (b) at section AA (80% rotor axial chord from LE)
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Entropy function contours from unsteady numerical simulations—(a) in a blade-to-blade plane at midspan, (b) across section AA
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Kinematic model illustrating the vortex transport through a turbine blade passage
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Comparison of vortex stretching ratio between analytical model and numerical simulations
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Effect of flow coefficient and stage loading coefficient on vortex tube kinetic energy ratio

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