Design Approach for an Optimum Prop-Fan Propulsion System PUBLIC ACCESS

[+] Author Affiliations
Gerald L. Brines

Pratt & Whitney, East Hartford, CT

Paper No. 85-IGT-57, pp. V001T01A003; 6 pages
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME


The predicted potential performance of the Prop-Fan offers a major improvement in the energy efficiency of future, short-range to medium-range transports. This paper describes the approach taken in designing an optimum Prop-Fan propulsion system. Trade-offs in the configuration(s) and performance are discussed, as are the important aspects of integrating the propeller, gearbox, engine, inlet, exhaust, and nacelle. Realizing the impressive potential fuel savings of the Prop-Fan will require very careful engine/airframe integration. Design options that will be compared are: a single-rotation versus counter-rotation arrangement, a tractor versus pusher installation, and wing versus fuselage mounting. In summary, the performance of turbofan powered and Prop-Fan powered, short-haul transports will be compared in detail by using fuel burn, operating costs, and noise as criteria.

Copyright © 1985 by ASME
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