| 摘要 |
A gaseous-fuel rocket engine in which an expanding oxidizer driven turbine or electric motor drives the an axial gaseous-fuel turbine compressor. The oxidizer is subsequently injected into a gaseous-fuel duct surrounding the axial gaseous-fuel compressor and defining a gaseous-fuel path having an inlet. The gaseous-fuel and oxygen mixture is ignited and the burned gases are expanded through a converging-diverging exhaust nozzle.
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