| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustion chamber for a rocket engine, allowing the use of a wide range of materials and the reduction in weight and cost by reducing the thickness of a structural jacket. SOLUTION: This combustion chamber structure for the rocket engine comprises a combustion chamber liner 10 having a cooling channel and at least one each of manifolds 20, 30 for supplying coolant, particularly, extremely low temperature fuel and removing it. The manifolds are integrally brazed to the combustion chamber liner and a portion of the combustion chamber liner, not covered with the manifolds, is covered with the electrically plated structural jacket. COPYRIGHT: (C)2004,JPO |
