Cycle Analysis for Helicopter Gas Turbine Engines PUBLIC ACCESS

[+] Author Affiliations
A. D. Bewley

Royal Aerospace Establishment, Pyestock, Farnborough, Hants, UK

Paper No. 89-GT-328, pp. V002T02A018; 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


Over the years there have been steady improvements in helicopter engine performance — higher specific powers (power/unit air flow), lower specific fuel consumptions and improved power/weight ratios. The gains have been the result of improving materials and cooling technologies and better aerodynamic design methods. These advances have allowed higher combustor temperatures and component efficiencies, with direct benefit to both specific power and specific fuel consumption (sfc), and higher turbomachinery stage loadings. These higher loadings have mainly been exploited as a means of reducing stage numbers, leading to improved reliability and maintainability and lower acquisition cost — always particularly strong goals in the helicopter field.

Copyright © 1989 by ASME
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