Continuing interest in fuel efficient Prop-Fan propulsion has highlighted the need for a large horsepower advanced technology turboprop engine. The initial application could be in a 100-150 passenger short/medium range aircraft. An engine concept which could provide from 9000 to 25000 SHP for commercial and military applications, and which could be available for introduction to service by 1990, is described. Results of engineering studies which support the preliminary design of the power unit and the approach being taken to defining the reduction gear are presented. Key technology issues related specifically to the propulsion system are identified. (Wassmann)
Turboprop engine propulsion for the 1990's
Propellerturbinentriebwerk fuer die neunziger Jahre
AIAA-Papers ; 1-8
1981
8 Seiten, 12 Bilder, 2 Tabellen, 5 Quellen
Conference paper
English
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