THRUST AUGMENTATION OF A TURBOJET ENGINE BY THE INTRODUCTION OF LIQUID AMMONIA INTO THE COMPRESSOR INLET

摘要

An experimental investigation was conducted to determine the thrust augmentation possible by the injection of liquid ammonia into the com¬pressor inlet of an axial-flow-type turbojet engine„ The flight condi-tions simulated were an altitude of 35,000 feet and a Mach number of 1=0. Ram air temperatures of 80° F and -40° F were used in addition to the standard ram air temperature of 13° F.nThe maximum net thrust augmentation obtained at the standard inlet (ram) air temperature was 13 percent at an ammonia-air ratio of 0.049 pound of ammonia per pound of air, corresponding to an augmented liquid ratio of 3.8. With 80° F inlet-air temperature, 29 percent aug¬mentation was obtained at an ammonia-air ratio of 0.055 pound of ammo¬nia per pound of air, corresponding to an augmented liquid ratio of 4.5.