| abstract |
Injection element in coaxial design for rocket combustion chambers with a combustion chamber pressure of 5 to 25 bar and for operation with two hypergol-reactive fuels, with a central body (2) for the oxidizer, the flow channel of which has a swirl body (4) and a conically widening outlet (5) with a sharp one Mouth edge (6), and with a concentrically surrounding the central body (2) in the outlet area and - forming a pre-reaction chamber (10) - towards the combustion chamber projecting sleeve for the admixture of the fuel, which lateral inflow openings (8) and a central, in Has area of the pre-reaction chamber circular cylindrical channel (9). The ratio of the length L to the diameter D of the pre-reaction space is 0.4 to 0.8. When entering the pre-reaction space, the speed of each fuel component is a minimum of 5 m / s and a maximum of 12 m / s, the ratio of the speed of the fuel to the speed of the oxidizer is 0.7 to 1.3. |