AFTERBURNER WITH CONTINUOUS DETONATION OF LIQUID FUEL

Abstract

The results of a new series of test ¦res of a detonation afterburner as part of turbojet engine are presented. In contrast to previous tests with a sequential arrangement of turbojet and afterburner [1], the new series provides for gasdynamic separation of air§ows: air is supplied to the afterburner separately using an auxiliary power unit simulating the bypass air§ow in a turbofan engine (Fig. 1). The separation of air§ows made it possible to ensure stable operation of the combined power plant in di¨erent modes of operation of the turbojet engine when the afterburner was turned on. In test ¦res, a stable mode of spinning detonation of aviation kerosene with single detonation wave was registered with a characteristic rotation frequency of 2 kHz (Fig. 2) and the detonative combustion of kerosene in the afterburner did not a¨ect the operation of the turbojet engine.