Patent ID: 6145299
Filing Date: 2000-11-14
Classification: F02K

Abstract:
A rocket engine comprising:a source of liquid fuel;a means for atomizing the liquid fuel in fluid communication with the source of liquid fuel;a chamber defined by a substantially enclosing chamber wall, the chamber disposed adjacent to the means for atomizing the liquid fuel in atomized fuel receiving relationship;a source of liquid oxidizer;a ring mounted on the substantially enclosing chamber wall defining a plurality of apertures, the plurality of apertures connected to the source of liquid oxidizer, the plurality of apertures substantially surrounding the chamber and disposed to admit the liquid oxidizer into the chamber;a housing having at least one substantially conical wall;a plurality of members attached to the housing in substantially radial array, and disposed within the chamber, and each of the plurality of members attached to the chamber walls holding the housing in fixed position with respect to the chamber;a conical surface disposed within the chamber, the surface forming substantially the top portion of the housing;a substantially annular passage defined by the wall of the housing and the substantially enclosing chamber wall, the combustion gasses passing through the annular passage, out to the ambient surroundings of the rocket.