| 摘要 |
A hybrid expander cycle rocket engine with separate turbopumps for a fuel and an oxidizer, where the fuel pump is driven by gaseous fuel passed from the fuel pump and through a heat exchanger formed within the nozzle or combustion chamber and passed through the fuel turbine and then into the combustion chamber. The oxidizer turbopump is driven by the gas generator with the fuel diverted from the fuel pump and burned with some of the oxidizer from the oxidizer pump. |
