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Preliminary Design of Low Cost Propulsion Systems Using Next Generation Cost Modeling Techniques FREE

[+] Author Affiliations
J. L. Younghans, R. M. Donaldson, D. R. Wallace, L. L. Long, R. B. Stewart

GE Aircraft Engines, Cincinnati, OH

Paper No. 98-GT-182, pp. V002T02A003; 8 pages
doi:10.1115/98-GT-182
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7863-7
  • Copyright © 1998 by ASME

abstract

At GE Aircraft Engines (GEAE), during the preliminary design process for aircraft propulsion systems, the designer has always been concerned about the cost implications of engine architecture and material requirements, which are driven by design specified engine thermodynamic operating conditions. The concern was not only about initial acquisition economics, but about maintenance costs associated with the propulsion life cycle as well as the development costs associated with design and certification of the power plant. The difficulty has been that there was no rapid, accurate cost estimating process to allow the designers ready access to the cost implications of design choices. High cycle pressure ratios and bypass ratios were thermodynamically attractive in reducing SFC. Technology, whether in the form of complex aerodynamic blade shapes to increase efficiency or higher temperature materials to reduce undesirable effects of cooling flows on SFC, was considered without in depth quantitative cost impacts of these design choices.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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