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TECHNICAL PAPERS

Evolution of Upstream Propagating Shock Waves From a Transonic Compressor Rotor

[+] Author and Article Information
Anil Prasad

Aerodynamics Division, Pratt and Whitney Aircraft Engines, East Hartford, CT 06108

J. Turbomach 125(1), 133-140 (Jan 23, 2003) (8 pages) doi:10.1115/1.1516813 History: Received October 28, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Locus of the passage centerline overlayed on contours of normalized static pressure in (a), and the variation of static pressure along the passage centerline in (b), for the 2-D inviscid computation
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Definition of axial line along which static pressure is interpolated, with contours of unit relative Mach number
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Axial pressure variations from the 2-D inviscid and viscous simulations are shown as solid lines, with the corresponding envelopes predicted from the semi-analytical model being shown with broken lines
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Comparison between measurement and 3-D viscous computation along the passage centerline at 92% span of (a) normalized total velocity, and (b) relative yaw angle. Experimental data are denoted by symbols and the solid lines correspond to the two consecutive computational planes between which the measurements lie.
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Axial pressure variations from the 3-D viscous and inviscid simulations are shown as solid lines, with the corresponding envelopes predicted from the semi-analytical model shown with broken lines
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Axial variation of normalized mass-averaged entropy due to the upstream propagating shock system (–) and the total entropy generated by the rotor ([[dashed_line]]). Results from the 3-D viscous simulation are displayed.
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Upstream variation of normalized circumferential static pressure distortion at four spanwise locations with the indicated inlet relative Mach numbers, from the 3-D viscous simulation
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Circumferential variation of normalized total velocity at (a) 80% span and 5% chord upstream of the leading edge, and (b) 92% span and 38% chord upstream of the leading edge. The solid line is the prediction from the 3-D viscous simulations and the symbols represent experimental data.
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Variation of the induced circumferential pressure distortion from an (steady) isolated rotor calculation compared to the same rotor embedded in a (time-accurate) multi-stage simulation. Results from 3-D viscous simulations are shown.

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