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Performance Improvement Features of General Electric Turbofan Engines PUBLIC ACCESS

[+] Author Affiliations
D. J. Lennard, W. A. Fasching

General Electric, Cincinnati, OH

Paper No. 82-GT-270, pp. V002T02A017; 7 pages
doi:10.1115/82-GT-270
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7957-3
  • Copyright © 1982 by ASME

abstract

Soaring fuel costs have triggered the development of a new generation of aircraft propulsion systems as well as performance modifications to current systems. This paper presents performance improvement features for General Electric turbofan engines that have either been developed or are being developed for commercial use. A number of these performance improvement features were the direct result of technology developed under the sponsorship of the National Aeronautic and Space Administration’s Engine Component Improvement (ECI) Program and the evolution of some of these performance improvement features is traced through current and future engines. Discussions will be directed toward performance features such as fan and exhaust nozzle aerodynamics improvements, improved turbomachinery clearance control, reduced flowpath losses, and high efficiency turbine cooling.

Copyright © 1982 by ASME
Topics: Engines , Turbofans
This article is only available in the PDF format.

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