| 摘要 |
A rocket engine includes a thrust chamber having a cooling channel, which is adapted to provide sustained cracking conditions for a fluid (e.g., kerosene) within the cooling channel under steady-state engine operating conditions. An augmenter having a fluid input communicates with an output of the cooling channel, and an output of the augmenter is in fluid communication with a turbine. A pump is mechanically coupled to the turbine, and provides fluid flow to the inlet of the cooling channel. |
