Rocket engine tubular chamber with single piece jacket

Details Rocket engine tubular chamber with single piece jacket Rocket engine tubular chamber with single piece jacket

2006-05-30

2006-05-30

Freay, Charles G. (Department: 3746)

Power plants

Reaction motor

Liquid oxidizer

C060S267000, C029S890010

Reexamination Certificate

active

07051513

ABSTRACT:
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.

REFERENCES:
patent: 3390986 (1968-07-01), Stenerson
patent: 3460759 (1969-08-01), Gregory et al.
patent: 3768256 (1973-10-01), Butter et al.
patent: 3897316 (1975-07-01), Huang
patent: 5557928 (1996-09-01), Castro et al.
patent: 6134782 (2000-10-01), Wright
patent: 0 697 515 (1966-02-01), None
patent: WO 95/29785 (1995-11-01), None

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