Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines

[+] Author and Article Information
L. He, T. Chen

School of Engineering, University of Durham, Durham, DH 1 3LE, UK

R. G. Wells, Y. S. Li, W. Ning

Compressor Group, Industrial Gas Turbines, ALSTOM Power, Lincoln, LN5 7FD, UK

J. Turbomach 124(4), 564-571 (Nov 07, 2002) (8 pages) doi:10.1115/1.1508382 History: Received September 21, 2001; Online November 07, 2002
Copyright © 2002 by ASME
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Meridional mesh for ALSTOM 2.5-stage compressor
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Performance lines calculated by baseline steady solver
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Entropy contours on midspan section (left: whole domain, right: close-up)
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Entropy contours on stator-1/rotor-2 interface (viewed from upstream, superimposed wakes shed from radial stator-1 and anticlockwise leaned rotor-1 blades) (a) stator-1 exit plane; (b) rotor-2 inlet plane
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Time-averaged efficiency variation due to stator-stator clocking—(a) 80% rotor speed; (b) 100% rotor speed
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Time-averaged efficiency/loss in 21 passages of rotor-2 (original rotor-rotor blade counts, 17:21)—(a) subsonic flow (80% speed); (b) transonic flow (100% speed)
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Efficiency variation due to rotor-rotor clocking (2-D mid-span section, rotor-rotor blade counts 21:21)—(a) subsonic flow; (b) transonic flow
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Entropy contours at rotor-rotor clocking positions with maximum and minimum losses in subsonic flow (rotor1-stator1-rotor2 configuration—(a) minimum loss; (b) maximum loss
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Entropy contours at rotor-rotor clocking positions with maximum and minimum losses in transonic flow (rotor1-stator1-rotor2 configuration)—(a) minimum loss; (b) maximum loss




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