| 摘要 |
The method involves making separately two subassemblies (20, 30) of welded shells by butt-welding the shells. An intermediate connection ring (14) is welded at an end of the subassembly (20) by orbital welding using laser, where the ring has a cylindrical mounting surface. An end of the subassembly (30) is engaged on the surface and is welded to the ring. Two connection rings (12, 22) are butt-welded with other ends of the subassemblies, respectively. Independent claims are also included for the following: (1) a combustion chamber comprising preformed shells (2) a turbojet comprising a combustion chamber. |
