F110-GE-132: Enhanced Power Through Low-Risk Derivative Technology

[+] Author and Article Information
A. R. Wadia, F. D. James

Large Military Engine Systems Design and Integration, GE Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 123(3), 544-551 (Feb 01, 2000) (8 pages) doi:10.1115/1.1378301 History: Received February 01, 2000
Copyright © 2001 by ASME
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Andersen, R. H., 1990, “F110: Power for the 90’s and Beyond,” ASME Paper No. 90-GT-SSS.
Kandebo, S. W., 1996, “GE Developing Longer-Life F110,” Aviat. Week Space Technol., Feb., pp. 42–43.
Wadia,  A. R., and Law,  C. H., 1993, “Low Aspect Ratio Transonic Rotors: Part 2—Influence of Location of Maximum Thickness on Transonic Compressor Performance,” ASME J. Turbomach., 115, pp. 226–239.
Hemsworth, M. C., 1969, “Development and Experiences of the First High-Bypass Ratio Engine, TF-39,” Paper No. 21, presented at the 11th Anglo-American Aeronautical Conference, London.
Rubbert, P. E., Boctor, M. L., Cowan, S. J., and Laprete, R. D., 1972, “Concept and Design of Stators Tailored to Shield a Fan From Pressure Disturbances Arising in the Downstream Fan Ducts,” AIAA Paper No. 72–84.
Wadia,  A. R., Szucs,  P. N., and Gundy-Burlet,  K. L., 1999, “Design and Testing of Swept and Leaned Outlet Guide Vanes to Reduce Stator-Strut-Splitter Aerodynamic Flow Interactions,” ASME J. Turbomach., 121, pp. 416–427.
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F110 engine model product development roadmap
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Reliability and thrust growth provide flexibility to satisfy a wide range of future customer requirements
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F110-GE EFE new features
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F110-GE-132 average thrust ratings on a standard day: (a) max A/B power; (b) intermediate rated power (dry)
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Fan efficiency technology comparison
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F110-GE-132 fan design features: EFE fan is physically interchangeable with current production EFE fan. No change in airframe/engine interface is required as the inlet diameter is identical between the two fans.
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F110-GE-132 assembled blisk fan rotor. The blisk fan produces reliability improvements over the current system by eliminating potential sources of high stress regions such as blade dovetails and midspan shrouds.
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EFE stage 1 fan blade with thicker blade leading edge
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Three-dimensional pictorial view of the closely coupled fan frame and exit guide vane system
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Entropy contours along the fan frame strut, splitter, and exit guide vanes showing stator wake streaks along the splitter surfaces and outer and inner endwall surfaces
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Instrumented EFE blisk installed in the F110 engine for aeromechanical qualification
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F110-GE-132 radial augmentor features
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Calculated velocity vectors for the current production F110-GE-129 augmentor
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Calculated velocity vectors for the F110-GE-132 radial augmentor
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Calculated temperature contours for the F110-GE-132 radial augmentor at a prescribed flight condition
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Comparison of the F110-GE baseline exhaust nozzle feature with the AVEN ready exhaust nozzle features
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F110-GE-132 optional ejector nozzle features




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