Reinigungsvorrichtung für Verbrennungsrückstände eines Raketen-Triebwerks

The present invention relates to a device for purging combustion residues from a thruster that comprises firstly a combustion chamber designed to receive a solid propellent and secondly a nozzle for evacuating propulsion gases and connected to the bottom of said chamber while leaving an annular space in which liquid residues of propellent combustion can accumulate. The device comprises at least one tube fixed on the converging part of the nozzle by fixing means, said tube including a first end dipped in the mass of liquid formed by said combustion residues and at a determined distance j from the bottom of the chamber, and a second end emerging level with the top end of the converging part and set back a little from the throat of the nozzle.