| 摘要 |
The invention relates to power plants, in particular to devices for mixing and atomizing propellant components, and may be used for development injection elements and injector heads of liquid-fuel rocket engines (LRE). The task of the invention is to increase the propellant component combustion efficiency via the increase of propellant component contact area. This task is solved by provision of radial grooves 3 in the outlet portion of a hollow tip 1 of the coaxial-jet injection element, the said hollow tip connecting the cavity of one propellant with the combustion zone, a sleeve 5 surrounding the said tip providing an annular gap 4 connecting the cavity of another propellant with the combustion zone. The sleeve inner surface outlet portion is equidistant relatively to the tip grooves outer surface, and the outlet cross-section area between the sleeve equidistant surface and the tip grooves is F<SUB>r</SUB>=(0,6-2,2)F<SUB>o</SUB>, where F<SUB>o </SUB>is the groove cross-section area at the tip outlet, 2 dependent claims, 3 Figures.
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