Advanced Core Technology: Key to Subsonic Propulsion Benefits PUBLIC ACCESS

[+] Author Affiliations
Arthur J. Glassman, Christopher A. Snyder, Gerald Knip, Jr.

National Aeronautics and Space Administration, Cleveland, OH

Paper No. 89-GT-241, pp. V002T02A005; 8 pages
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7914-6
  • Copyright © 1989 by ASME


A study was conducted to identify the potential performance benefits and key technology drivers associated with advanced cores for subsonic high-bypass turbofan engines. Investigated first were the individual sensitivities of varying compressor efficiency, pressure ratio and bleed (for turbine cooling); combustor pressure recovery; and turbine efficiency and inlet temperature on thermal efficiency and core specific power output. Then, engine cycle and mission performance benefits were determined for systems incorporating all potentially achievable technology advancements.

The individual thermodynamic sensitivities are shown over a range of turbine temperatures (at cruise) from 2900 to 3500 °R and for both constant (current technology) and optimum (maximum thermal efficiency) overall pressure ratios. It is seen that no single parameter by itself will provide a large increase in core thermal efficiency, which is the thermodynamic parameter of most concern for transport propulsion. However, when all potentially achievable advancements are considered, there occurs a synergism that produces significant cycle and mission performance benefits. The nature of these benefits are presented and the technology challenges associated with achieving them are discussed.

Copyright © 1989 by ASME
Topics: Propulsion
This article is only available in the PDF format.



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