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TECHNICAL PAPERS

Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design

[+] Author and Article Information
John J. Adamczyk

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 122(2), 189-217 (Feb 01, 1999) (29 pages) doi:10.1115/1.555439 History: Received February 01, 1999
Copyright © 2000 by ASME
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Figures

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The range of mathematical models that can be used to simulate turbomachinery flows
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Spanwise distribution of total temperature down-stream of a high-speed compressor rotor
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Radial transport of rotor wake fluid particles
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(a) Total temperature exiting a high-speed compressor rotor at an instant of time; (b) time history of radial velocity and total temperature downstream of a compressor rotor
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Kerrebrock and Mikolajczak effect in a turbine stage
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Convection of a hot streak through a turbine cascade
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Snapshot of unsteady total temperature ratio exiting a turbine rotor
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Turbine blade temperature distribution
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Wake blade row interactions in a typical turbine and compressor
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Overall pressure coefficient for the NASA-Lewis low-speed four-stage axial compressor
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Individual stage pressure rise coefficient as a function of inlet flow coefficient for the NASA-Lewis low-speed four-stage axial compressor
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Axisymmetric flow variables exiting the second-stage stator in the NASA-Lewis low-speed four-stage axial compressor
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Axisymmetric flow variables exiting the third-stage rotor in the NASA-Lewis low-speed four-stage axial compressor
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(a) Comparison of total temperature as predicted by APNASA and CAFMIX II for the ten-stage GE90 compressor; (b) comparison of total pressure as predicted by APNASA and CAFMIX II for the ten-stage GE90 compressor
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(a) Spanwise distribution of total pressure at the exit of the stage 3 stator in the GE90 compressor; (b) spanwise distribution of total temperature at the exit of the stage 3 stator in the GE90 compressor; (c) spanwise distribution of total pressure at the exit of the stage 7 stator in the GE90 compressor; (d) spanwise distribution of total temperature at the exit of the stage 7 stator in the GE90 compressor; (e) spanwise distribution of total pressure at the compressor exit in the GE90 compressor; (f) spanwise distribution of total temperature at the compressor exit in the GE90 compressor
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Flow blockage distribution through the GE90 compressor
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(a) Relative flow angle at the exit of the stage 3 rotor in the GE90 compressor; (b) absolute flow angle at the exit of the stage 3 stator in the GE90 compressor; (c) relative flow angle at the exit of the stage 7 rotor in the GE90 compressor; (d) absolute flow angle at the exit of the stage 7 stator in the GE90 compressor
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Percent difference in total pressure ratio through the GE90 compressor near the design speed operating point
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(a) Spanwise distribution of total pressure at the exit of the stage 3 rotor in the GE90 near design speed; (b) spanwise distribution of total temperature at the exit of the stage 3 rotor in the GE90 near design speed; (c) spanwise distribution of total pressure at the exit of the stage 7 rotor in the GE90 near design speed; (d) spanwise distribution of total pressure at the exit of the stage 7 rotor in the GE90 near design speed; (e) spanwise distribution of total pressure at the exit of the GE90 near design speed; (f) spanwise distribution of total temperature at the exit of the GE90 near design speed
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Percent difference in stage pressure ratio as a function of bleed rates for the GE90 compressor
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Percent difference in stage pressure ratio as a function of back pressure for the GE90 compressor
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(a) Stage total pressure ratio characteristic as a function of corrected mass flow for a three-stage high-speed compressor; (b) stage total temperature ratio characteristic as a function of corrected mass flow for a three-stage high-speed compressor
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(a) Spanwise distribution of total pressure at the exit of the stage 1 rotor for a three-stage high-speed compressor; (b) spanwise distribution of total temperature at the exit of the stage 1 rotor for a three-stage high-speed compressor
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(a) Spanwise distribution of total pressure at the exit of the stage 3 rotor for a three-stage high-speed compressor; (b) spanwise distribution of total temperature at the exit of the stage 3 rotor for a three-stage high-speed compressor
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(a) Total pressure profile at the exit of an HP turbine stage 2 rotor; (b) total temperature profile at the exit of an HP turbine stage 2 rotor
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(a) Total pressure profile at the exit of an LP turbine; (b) total temperature profile at the exit of an LP turbine
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Overall pressure coefficient as a function of inlet flow coefficient for the NASA-Lewis four-stage axial flow compressor
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Steady flow through a cascade with blockage

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