| 摘要 |
<p>An injector element (1) of coaxial design is provided for a rocket drive for operation with a first and a second propellant, comprising a central body (5), a sleeve (2) and a flow splitter (7). The central body (5) comprises a flow channel with an outlet, the central body (5) generating a conical drop distribution at the outlet forming a fuel cone, wherein the first propellant, normally an oxidant, is provided in the central body (5). The sleeve (2) concentrically surrounds the central body (5) to form an annular flow channel for the second propellant, normally fuel. The flow splitter (7) is arranged between the central body (5) and the sleeve (2) for splitting the second propellant into a plurality of individual flows. The flow splitter (7) includes a given number of passage channels which are distributed around the central body (5), each of the passage channels for generating a fine propellant jet. The passage channels are formed between annular rings (18, 19) extending towards each other to provide sharp circumferential edges to the passage channels, a first of the rings (18, 19) being part of the central body (5) and a second of the rings (18, 19) being part of the sleeve (2), wherein one of the first and the second annular rings (18, 19) having protrusions (20, 21) which are distributed around the central body (5) and adjoin to the other annular ring.</p> |
