| 摘要 |
A fluid cooled rocket, comprises a tubular housing which forms an interior combustion chamber which has a closed end formed by a head containing a propellant component injector, and an opposite opened end forming a thrust gas discharge. The housing side walls define an interior combustion chamber of uniform diameter, adjacent the closed head, is formed into an inwardly converging portion, a nozzle neck portion of smallest diameter, and an outwardly diverging portion, all proceed in a direction from the closed end toward the opposite gas discharge open end. The inwardly converging portion and the nozzle neck portion, and at least a part of the diverging portion, is formed with a first wall construction having a plurality of circumferentially arranged longitudinally extending first cooling channels, which are connected at the ends adjacent the opened discharge end with an annular inlet duct and at the end adjacent the closed head, with an annular discharge duct, which is advantageously connected to the injector. The first cooling channels are therefor connected in a closed circuit from the supply pump to the injector. At least one second set of cooling channels are formed in at least a part of the remaining portion of the divergent section, and their outer ends are opened to discharge in the direction of thrust. The inner ends of the second cooling channels are connected to an inlet which, for example, may be formed directly adjacent the inlet for the first cooling channel and which may be connected so as to be bled from a portion of the flow to the first cooling channel, with the quantity of flow being much less. The construction advantageously includes abutting flanges of the sections forming the distinct cooling channels with one flange being formed integral with the inlet for the first cooling channels and with a nozzle flow passage defined between the annular inlet duct of the first cooling passage to an annular flow space defined in the flange of the second cooling channel portion. The construction may also include an intermediate section between the first and second cooling channels in the divergent portion of the combustion chamber walls.
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