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TECHNICAL PAPERS

Aerodynamic Design and Testing of an Axial Flow Compressor With Pressure Ratio of 23.3:1 for the LM2500+ Gas Turbine

[+] Author and Article Information
A. R. Wadia, D. P. Wolf, F. G. Haaser

GE Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 124(3), 331-340 (Jul 10, 2002) (10 pages) doi:10.1115/1.1464562 History: Received January 01, 1999; Revised January 24, 2002; Online July 10, 2002
Copyright © 2002 by ASME
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References

Figures

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LM2500+ gas turbine unique features
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LM2500+ high pressure compressor improvements relative to the base (LM2500) compressor
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Comparison of Stage 0 blade exit radial profiles of total pressure, total temperature, and adiabatic efficiency at the aerodynamic design point
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LM2500+ Rotor 0 isentropic Mach number contours on the pressure and suction surfaces
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LM2500+ Rotor 0 blade passage shock structure at 8 and 45% immersions
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Axial distribution of blade surface isentropic Mach number near the hub for LM2500+ Rotor 0
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Axial distribution of Stage 0 vane surface isentropic Mach number
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Axial distribution of blade surface isentropic Mach number for Rotor 1
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Comparison between the LM2500+ wide chord Rotor 1 and the LM2500 Rotor 1 with the midspan shroud
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LM2500+ compressor stator schedule
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LM2500+ compressor pretest variable stator gang relation
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LM2500+ compressor performance with pretest variable stator schedule
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LM2500+ compressor performance with “stress rig” variable stator schedule
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LM2500+ IGV-Rotor 0 performance
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LM2500+ “rear block” performance
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LM2500+ compressor open stator stall test results

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