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Injection element for injecting cryogenic liquid propellant mixture into e.g. single-element combustion chamber of rocket engine, has annular pipe injecting propellant into chamber and enclosing central body having mixture ignition device
Injection element for injecting cryogenic liquid propellant mixture into e.g. single-element combustion chamber of rocket engine, has annular pipe injecting propellant into chamber and enclosing central body having mixture ignition device
The element (201) has first and second annular pipes (206, 207) injecting two cryogenic liquid propellants (E1, E2) into combustion chambers, respectively, where the second annular pipe is arranged coaxial to and outwardly adjacent to the first annular pipe. The first annular pipe encloses a central body (205). The central body comprises a direct propellant mixture ignition device formed with a cavity (209) that communicates with a hot fluid source and with an external surface (210) of the central body through an oblique opening (211) to inject hot fluid e.g. hot gas, in the chambers. The hot fluid source is a pyrotechnic device or a torch. An independent claim is also included for a method for igniting propellant mixture in a combustion chamber.
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