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Ideal Power Output — An Alternative Aircraft Engine Performance Comparator PUBLIC ACCESS

[+] Author Affiliations
Marvin F. Schmidt

Universal Technology Corporation

Christopher M. Norden, Jeffrey M. Stricker

USAF/WL/POTA

Paper No. 97-GT-228, pp. V001T01A004; 5 pages
doi:10.1115/97-GT-228
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7868-2
  • Copyright © 1997 by ASME

abstract

The gas turbine is applied in four basic configurations; the turbojet, the turbofan, the turboprop and the turboshaft. Comparisons of the performance of these various configurations is difficult since they convert the energy to different forms, i.e. thrust or shaft power. Cycle variables which do not necessarily constitute advancements in the state-of-the-art such as bypass ratio and fan pressure ratio can have a profound effect on thrust and shaft power. Differences in flight speed and altitude capability further confound the comparisons. What is required is a comparison methodology that removes all of these variables and yet puts all the various types of engines on an equitable basis. This paper will provide such a comparison tool. All turbomachinery, regardless of configuration, can be compared with this method.

Copyright © 1997 by ASME
This article is only available in the PDF format.

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