HYBRID-CYCLE LIQUID PROPELLANT ROCKET ENGINE

摘要

Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.

主权项

1. A hybrid rocket engine comprising:
a first pump powered by a first turbine; a second pump powered by a second turbine; a gas generator connected to the first pump and the second pump, wherein an output of the gas generator is connected to the first turbine and the second turbine to provide mechanical power to the first pump and the second pump; a third pump powered by a third turbine; a fourth pump powered by a fourth turbine; and a nozzle comprising an expander cycle in a wall and a combustion chamber; wherein an output of the third pump is connected to the expander cycle, and an output of the expander cycle is connected to the third turbine and the fourth turbine to provide mechanical power to the third pump and the fourth pump, and wherein an output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.