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Preliminary Study of Advanced Turboprops for Low Energy ConsumptionThe fuel savings potential of advanced turboprops (operational about 1985) was calculated and compared with that of an advanced turbofan for use in an advanced subsonic transport. At the design point, altitude 10.67 km and Mach 0.80, turbine-inlet temperature was fixed at 1590 K while overall pressure ratio was varied from 25 to 50. The regenerative turboprop had a pressure ratio of only 10 and an 85 percent effective rotary heat exchanger. Variable camber propellers were used with an efficiency of 85 percent. The study indicated a fuel savings of 33 percent, a takeoff gross weight reduction of 15 percent, and a direct operating cost reduction of 18 percent was possible when turboprops were used instead of the reference turbofan at a range of 10 200 km. These reductions were 28, 11, and 14 percent, respectively, at a range of 5500 km. Increasing overall pressure ratio from 25 to 50 saved little fuel and slightly increased takeoff gross weight.
Document ID
19750016667
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kraft, G. A. (NASA Lewis Research Center Cleveland, OH, United States)
Strack, W. C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8371
NASA-TM-X-71740
Accession Number
75N24739
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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