Injection element of coaxial design for rocket combustion engines

A rocket combustion chamber injection element of coaxial design for operation with two propellants, including at least one propellant which disintegrates into drops only with difficulty as the consequence of low vapor pressure and/or high surface tension, including operation with nonhypergolic propellants, wherein liquid oxygen (LOX) is preferably used as the oxidant, and kerosene or monomethylhydrazine (MMH) is preferably used as the fuel, comprising:

• a central body for the more readily disintegrating propellant, normally the oxidant, the central body including a flow channel with an outlet, said flow channel including means for generating a conical drop distribution forming a fuel cone;
• a sleeve concentrically surrounding said central body to form an annular flow channel for said less readily disintegrating propellant, normally the fuel;
• and
• a flow splitter arranged between said central body and said sleeve, said flow splitter for splitting the propellant flow into a plurality of individual flows, said flow splitter including an even number of passage channels which are uniformally distributed around said central body, each passage channel defining means for generating a relatively fine propellant jet, said passage channels cooperating in pairs in terms of impact atomization for directing said relatively fine propellant jets to impinge, wherein an--imaginary--axis of two adjacent cooperating passage channels each intersect downstream of said flow splitter and upstream of a--imaginary--points of impact on said fuel cone discharged from said central body.