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TECHNICAL PAPERS

Axial Compressor Aerodesign Evolution at General Electric

[+] Author and Article Information
Leroy H. Smith

GE Aircraft Engines, Cincinnati, OH 45215e-mail: leroy.smith@ae.ge.com

J. Turbomach 124(3), 321-330 (Jul 10, 2002) (10 pages) doi:10.1115/1.1486219 History: Received November 14, 2001; Revised April 02, 2002; Online July 10, 2002
Copyright © 2002 by ASME
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References

Figures

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Compressor vector diagram calculation methods
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14 Stage Research Compressor rotor inlet swirl and axial velocity distributions
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J53 Compressor rotor inlet swirl and axial velocity distributions
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Methods used for design of series airfoils
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Airfoil custom tailoring methods
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Departure angle definition
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Circumferential-average meridional mach numbers in transonic rotor. Note overspeed at part-span shroud.
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Blade contoured at shroud to match circumferential-average flow angles
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Projected streamsurface geometry showing free-flow streamline and key area locations
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Throat area/capture area ratios for 12 streamlines at the design point
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Consequences of off-design operation for one streamline
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Internal contraction causes shock unstart at reduced speed
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Passage exit area needs to be large enough to provide subsonic diffusion to exit Mach number
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J93 Compressor flowpath. Note high aspect ratios.
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Low-speed research compressor tests showed significant aspect ratio effects
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Aspect ratio and solidity combinations tested
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Stall pressure rise correlation
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Dynamic pressure factor definition; stator example shown
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Test polytropic efficiencies compared with values calculated using CUS5 Code for GE multistage compressors designed before CFD

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