Fabrication of a rocket engine with transition structure between the combustion chamber and the injector

摘要

A rocket engine (20) is fabricated by a multistep brazing and welding technique. An annular step collar (46) is first brazed to a transition joint (56, 58). This first subassembly is second brazed to the combustion chamber (22). This second subassembly is third brazed to an annular adaptor (52) to form a third subassembly. The succeeding brazing steps are performed at successively lower temperatures. The third subassembly is welded to an injector (38). <IMAGE>