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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

Scalzo, A., and Mori, Y., 1988, “A New 150 MW High Efficiency Heavy Duty Combustion Turbine,” ASME, Paper No. 88-GT-162.
Kashiwabara, Y., Katoh, Y., Ishii, H., Hattori, T., Matsura, Y., and Sasada, T., 1990, “Developments Leading to an Axial Flow Compressor for a 25MW Class High Efficiency Gas Turbine,” ASME, Paper No. 90-GT-238.
Sehra, A., Bettner, J., and Cohn, A., 1991, “Design of a High Performance Axial Compressor for Utility Gas Turbine,” ASME, Paper No. 91-GT-145.
Smed, J., Pisz, F., Kain, J., Yamaguchi, N., Umemura, S., 1991, “501F Compressor Development Program,” ASME, Paper No. 91-GT-226.
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Stringham, G., Cassem, T., Prince, T., and Yeung, P., 1998, “Design and Development of a Nine Stage Axial Flow Compressor for Industrial Gas Turbines,” ASME, Paper No. 98-GT-140.
Farmer,  R., 1994, “GE Launches LM2500+ Rated at 39 MW and 38% Thermal Efficiency,” Gas Turbine World, May/June 1994, pp. 24–32.
Valenti,  M., 1998, “Luxury Liners Go Green,” ASME Mechanical Engineering, July, pp. 72–73.
Klapproth, J. F., Miller, M. L., and Parker, D. E., 1979, “Aerodynamic Development and Performance of the CF6-6/LM2500 Compressor,”AIAA, Paper No. 79-7030.
Eisenberg, B., 1993, “Development of a New Front Stage for an Industrial Axial Flow Compressor,” ASME, Paper No. 93-GT-327.
Katoh, Y., Kashiwabara, Y., Ishii, H., Tsuda, Y., and Yanagida, M., 1993, “Development of a Transonic Front Stage of an Axial Flow Compressor for Industrial Gas Turbines,” ASME, Paper No. 93-GT-304.
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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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