Turbojet-engine thrust augmentation at altitude by combined ammonia injection into the compressor inlet and afterburning

Useller, James W., Fenn, David B., Harp, James L., Jr.
naca-rm-e52l19
1953


An experimental investigation was conducted on an axial-flow turbojet engine operating at simulated transonic flight conditions at an altitude of 35,000 feet to determine the magnitude of the thrust augmentation and to ascertain the operational characteristics of a combined augmentation system. This system included the use of a high-performance afterburner (operating at approximately stoichiometric condition) and the introduction of liquid anhydrous ammonia into the compressor inlet (ammonia-air ratios from 0 to 0.55). The maximum augmented net thrust ratio obtained, 2.13, resulted from a combination of a stoichiometric condition in the afterburner and the introduction of liquid ammonia into the compressor inlet to produce an ammonia-air ratio of 0.045. Maximum afterburner combustion efficiency and temperature occurred while the afterburner was operating stoichiometrically both with and without the ammonia injection.

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