Optimum Cycle Parameters for Turbofan Engines PUBLIC ACCESS

[+] Author Affiliations
W. C. Moffatt

Royal Military College of Canada, Kingston, ON, Canada

Paper No. 70-GT-65, pp. V01AT01A065; 8 pages
  • ASME 1970 International Gas Turbine Conference and Products Show
  • Volume 1A: General
  • Brussels, Belgium, May 24–28, 1970
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7985-6
  • Copyright © 1970 by ASME


This paper presents closed-form solutions for optimum compressor pressure ratio, bypass ratio and fan pressure ratio, given the turbine inlet temperature, component efficiencies and flight Mach number for a turbofan engine. In addition a simple procedure is outlined for obtaining the optimum combination of these quantities and a sample calculation is included. The optimum condition is defined as that which maximizes the specific thrust (thrust per pound per second of air flow through the gasifier) of the engine. The effects of differing gas properties in different portions of the engine are included in the analysis.

Copyright © 1970 by ASME
Topics: Engines , Cycles , Turbofans
This article is only available in the PDF format.



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