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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 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, provi

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 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 and an exit manifold with a plurality of holes for receiving an end of each tube, inserting a brazing preform into each hole, inserting a first end of each tube into the inlet manifold and a second end of each tube into the outlet manifold so that the first end is surrounded by a first brazing preform and the second end is surrounded by a second brazing preform, and brazing the inlet and outlet manifolds to the tubes. 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 on exposed portions of the tubes and forming a single piece jacket construction around the tubes.

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What is claimed is: 1. 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; pr

What is claimed is: 1. 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. 2. The method according to claim 1, wherein said joining step comprises welding said ferrules to said tubes. 3. The method according to claim 1, wherein said joining step comprises brazing said ferrules to said tubes. 4. The method according to claim 1, further comprising: inspecting said brazed joints; and coating exposed portions of said tubes with a layer of coating material. 5. The method according to claim 4, wherein said coating step comprises electroplating said coating material onto said exposed portions. 6. The method according to claim 4, wherein said coating step comprises vacuum plasma spraying said coating material onto said exposed portions. 7. The method according to claim 4, further comprising: installing jacket sections over said layer of coating material; and joining said jacket sections to said manifolds and to each other to form a single piece jacket construction. 8. The method according to claim 7, wherein said joining step comprises welding said jacket sections to said manifolds and to each other. 9. The method according to claim 7, further comprising brazing said single piece jacket construction to said coated tubes. 10. The method according to claim 7, further comprising joining an end cap to said exit manifold and to said single piece jacket construction. 11. The method according to claim 7, further comprising joining exit manifold closeout sections to said single piece jacket construction. 12. A regeneratively cooled tubular construction rocket engine combustion chamber having a de Laval nozzle comprising: a plurality of tubes for conveying a coolant, each of said tubes being formed and shaped into the profile of said de Laval nozzle; an inlet manifold and an exit manifold; each of said tubes having a first end brazed to said inlet manifold and a second end brazed to said exit manifold; a layer of coating material on exposed portions of said tubes; a single piece jacket construction surrounding said tubes and said layer of coating material and being joined to said tubes; and a plurality of ferrules joined to said tubes. 13. A rocket engine combustion chamber according to claim 12, further comprising each of said tubes has a constantly expanding cross section in an upper chamber area. 14. A rocket engine combustion chamber according to claim 12, wherein said single piece jacket constructions includes a plurality of jacket sections joined together and joined to said inlet and exit manifolds. 15. A rocket engine combustion chamber according to claim 14, wherein said jacket sections include two 180 degree circumferential throat sections. 16. A rocket engine combustion chamber according to claim 12, further comprising an end cap joined to the exit manifold and the single piece jacket construction. 17. A rocket engine combustion chamber according to claim 12, further comprising exit manifold closeout sections joined to said single piece jacket construction.