| 摘要 |
A method of operating a liquid fuel rocket engine having at least first and second propellant component pumps, driven by a gas turbine which is connected to discharge its turbine propulsion gases through a secondary thrust nozzle, includes a main engine having a combustion chamber with a thrust nozzle, an initial expansion portion with an expansion corresponding to ground pressure and a final expansion portion connected to the initial expansion portion and terminating in a thrust discharge operating substantially at vacuum and with means for circulating at least one propellant component through cooling channels of the walls of both expansion portions, comprises, directing a first component into the combustion chamber, and directing at least a first portion of a second propellant component into the walls of the initial expansion portion and then into the combustion chamber and directing a second portion of the second propellant component into the walls of the final expansion portion so that they are heated therein and, thereafter, directing the heated propellant component gases into the turbine. The liquid fuel rocket engine for operation in outer space, comprises, wall means defining a combustion chamber having an injection head and a thrust nozzle part with a narrow neck portion, an initial expanding portion and a final expanding portion which terminates in a thrust discharge.
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