Experimental study on thrust augmentation of ejector driven by pulse detonation engine

We performed experimental studies of the ejector driven by a pulse detonation rocket engine using gasoline as fuel and air as oxidant in order to investigate the thrust augmentation performance of unsteady pulsejet coupling with complex shock wave and detonation combustion wave. The inner diameters of the detonation engine and the ejector with a convergent inlet were 60 mm and 120 mm respectively. The thrust augmentation was measured at eleven different positions at four operating frequencies of 15 Hz, 20 Hz, 25 z and 30 Hz. The experimental results indicated that the ejector was very effective in increasing the thrust of the system. The engine-ejector had a larger thrust augmentation when the ejector was located at the upstream of the engine exit. Peak thrust augmentation level was recorded to be approximately 158% at upstream position. The results also showed preliminarily that the thrust augmentation was increased with increasing operating frequency.