Rocket engine tubular chamber with single piece jacket

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.