| 摘要 |
Device for supplying fuel for a rocket propulsion unit has a first and at least a second fuel circuit for respective different fuels. Each fuel is brought to an increased energy level by a pump and is supplied for combustion by way of injection elements. The first fuel is heated in cooling channels extending in a propulsion chamber wall before the fuel is supplied for combustion, and the first fuel is subsequently fed to at least the turbines assigned to the pumps. A heat exchanger is provided in which the fuel coming from the turbines is in a heat exchange with a fuel coming from a pump. A heat exchanger especially usable in the device for supplying fuel is provided.
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