| 摘要 |
PURPOSE: To miniaturize a structure and to facilitate disassembly by allowing hot gas from a gas generator to flow to turbines of first and second turbopumps for supplying propellant at high pressure, and guiding discharged gas to a common exhaust duct. CONSTITUTION: High-temperature gas from a gas generator is injected from injectors 71, 72 by fixed structures 41 to 41 made of thermostructural composite materials and rotationally drives turbines 10, 20 of turbopumps 1, 2, and high- pressure propellant is fed to a rocket engine by pumps 12, 22. The discharged gas is allowed to flow to orifices 75, 78 and recovered into an exhaust duct 76 through a leakage preventing outer metallic cover 5. The pumps 12, 22 and the turbopumps 1, 2 are connected to one another by connecting parts 9 having radial pins. Therefore, the structure can be miniaturized, disassembly can be facilitated, and safety conditions can be satisfied.
|
