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.

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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