BURNING OF THE MIXTURE OF LIQUID KEROSENE AND AIR IN THE DETONATION CHAMBER 503 MM IN DIAMETER WITH VARIATIONS OF ITS GEOMETRY

Abstract

Regimes of continuous detonation of heterogeneous mixtures of aviation kerosene and air are obtained for the first time and studied in a flow-type annular cylindrical chamber 503 mm in diameter with variations of its geometry: air supply slot, kerosene injectors, and combustor geometry. The air flow rate is changed in the interval 8.4–33.7 kg/s, the kerosene flow rate is changed in the interval 1.38–2.05 kg/s, and the equivalence ratio is changed from 0.88 tO2.8. Kerosene is bubbled with air. Regimes of continuous multifront detonation (CMD) are observed in the case of combustor duct constriction at the exit. Based on the pressure measured at the combustor exit, specific impulses are determined. The maximum specific impulse with allowance for the energy of compressed air in the receivers is approximately 1400 s.