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Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet EnginesA theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by each method were determined. A comparison was also made for a given time of operation of the weight of an augmented engine plus fuel and additional liquids to the weight of a standard engine plus fuel producing the same thrust.
Document ID
20050080716
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Hall, Eldon W. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Wilcox, E. Clinton (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 22, 2013
Publication Date
October 27, 1948
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E8H11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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