A Computational Study of a Novel Turbine Rotor Partial Shroud

[+] Author and Article Information
Neil W. Harvey

Turbine Engineering, Rolls-Royce Plc, Derby, United Kingdom

Ken Ramsden

School of Mechanical Engineering, Cranfield University, Cranfield, United Kingdom

J. Turbomach 123(3), 534-543 (Feb 01, 2000) (10 pages) doi:10.1115/1.1370166 History: Received February 01, 2000
Copyright © 2001 by ASME
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Illustration of OTL and outer passage secondary flows for a shroudless turbine rotor
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Tip gap flow for an unshrouded blade 1
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Perspective view of a typical shroud top geometry for a Rolls-Royce civil HP turbine rotor
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Calculation grid for MT2. Blade-to-blade view 50 percent span.
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Calculation grid for MT2. Axial view+pressure side tip detail, 50 percent cax.
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Rotor cascade exit whirl angle profiles (40 percent cax downstream of trailing edge), from 45
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Comparison of measured and calculated rotor losses (as percent stage efficiency) for Rolls-Royce model rig turbines
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Comparison of tip static pressure for the MT2 rotor
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Calculation grid for MT2 winglet. Blade-to-blade view.
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MT2 rotor: Calculated OTL loss for plain tip and winglet
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Calculated static pressure distributions for MT2 rotor at 97.1 percent span, + “gutter” camberline at tip gap midheight
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Contours of calculated relative total pressure at the trailing edge grid planes for MT2 plain tip and winglet
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Visualization of calculated OTL flow for MT2 plain tip and winglet: plan view on tip
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Visualization of calculated OTL flow for MT2 plain tip and winglet: view on suction side
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Calculated exit whirl angle profiles for MT2 rotor, plain tip, and winglet, 60 percent cax downstream of trailing edge
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Comparison of outlines of winglet and typical Rolls-Royce HP turbine (plain-sided) rotor shroud, scaled to the same cax




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