Pulse detonation jet engine

Abstract

The invention relates to jet engines, in particular to pulse detonation jet engines. The required technical result, which consists in increasing the efficiency and reliability, is achieved in an engine with a combustion chamber which is structured as detonation resonator with an outlet to the exhaust nozzle. The resonator has form of an aspherical reflector symmetrical with respect to the engine axis. The engine uses gaseous fuels and gaseous oxidizer and single stage combustion process. In case of use of hydrocarbon fuel, the fuel conduit has a pyrolyzing chamber. Pyrolizing is achieved by contact of fuel flow with heated back side of said reflector. A mixture of fuel and oxidizer is supplied into the combustion chamber through an annular supersonic injection system. To initiate detonation, these engines may have a detonation initiator in the form of a tube plugged at the distal end and open at the end inserted into the combustion chamber and located along the axis of the engine. Detonation products ejected through the exhaust nozzle create thrust that pushes the engine in the opposite direction. This design of the pulse detonation jet engine is simple, reliable and allows achieving high efficiency of generation of thrust propulsion force thanks to maintaining cyclic resonant detonation at a frequency of around 10 kHz.

Dependencies are inferred from the claim text.