Rocket engine tubular combustion chamber with single piece jacket

A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes 22 formed and shaped into the profile of a nozzle with each of the tubes having a constantly expanding cross section in an upper chamber area, providing an inlet manifold 32 and an exit manifold 30 with a plurality of holes 29 for receiving an end of each tube 22, inserting a brazing preform 31 into each hole 29, inserting a first end of each tube 22 into the inlet manifold 32 and a second end of each tube 22 into the outlet manifold 30 so that the first end is surrounded by a first brazing preform 31 and the second end is surrounded by a second brazing preform 31, and brazing the inlet and outlet manifolds 32,30 to the tubes 22. The brazing step forms a series of brazed joints between the tubes and the manifolds. The method further includes the steps of forming a layer of coating material 34 on exposed portions of the tubes 22 and forming a single piece jacket construction 36 around the tubes 22.