Patent ID: 7051513

Claim:
A method for forming a coolant system for a rocket engine combustion chamber comprising the steps of: providing a plurality of tubes formed and shaped into the profile of a nozzle with each of said tubes having a constantly expanding cross section in an upper chamber area; providing an inlet manifold and an exit manifold with a plurality of holes for receiving an end of each said tube; providing a plurality of ferrules; inserting a brazing preform into each said hole; inserting a first end of each said tube into said inlet manifold and a second end of each said tube into said outlet manifold so that said first end is surrounded by a first brazing preform and said second end is surrounded by a second brazing preform; brazing said inlet and outlet manifolds to said tubes, said brazing step forming a series of brazed joints between said tubes and said manifolds; and joining said ferrules to said tubes prior to said tube inserting step so as to form a tube assembly.