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US 5,701,670 AGranted
Method of making rocket engine combustion chamber utilizing "slide in" port liner
AssigneeBoeing North American, Inc.
InventorsSteven C. Fisher, Theodore C. Adams, Maynard L. Stangeland, Jacob Rietdyk, Paul R. Winans
Life of this patent
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Abstract
A method of fabricating a rocket engine combustion chamber comprising assembling a liner having cooling channels, a plurality of throat support sections, and a structural jacket having inlet and outlet manifolds. Then heating the assembly in a pressurized furnace to bond the assembled parts to each other.
Claims9
A method of making a rocket engine combustion chamber comprising:
- forming a coolant liner having an outside surface;
- forming a plurality of coolant channels on the outside surface of the coolant liner so that the surface has a plurality of lands;
- forming at least two throat support sections;
- assembling the throat support sections together around the outside surface of the coolant liner;
- forming a structural jacket having an inside cavity, an inlet manifold, inlet feed passages, an outlet manifold, and outlet feed passages;
- inserting the coolant liner with surrounding throat support sections into the structural jacket inside cavity to form a combustion chamber assembly;
- forming sealing joints between the coolant liner and the structural jacket to seal off the coolant channels;
- capping the inlet and outlet manifolds;
- inserting the combustion chamber assembly into a pressure furnace;
- pressurizing the furnace, thus forcing the coolant liner, throat support sections, and structural jacket into contact;
- heating the combustion chamber assembly to a bonding temperature for bonding the assembled parts to each other to form the combustion chamber while pressurizing the pressure furnace.
8 more elements
A method of making a rocket engine combustion chamber comprising:
- forming a closed out coolant liner having an outside surface;
- forming at least two throat support sections;
- assembling the throat support sections together around the outside surface of the coolant liner;
- forming a structural jacket having an inside cavity, an inlet manifold, inlet feed passages, an outlet manifold, and outlet feed passages;
- inserting the coolant liner with surrounding throat support sections into the structural jacket inside cavity to form a combustion chamber assembly;
- forming sealing joints between the coolant liner and the structural jacket to seal off the coolant channels;
- capping the inlet and outlet manifolds;
- inserting the combustion chamber assembly into a pressure furnace;
- pressurizing the furnace, thus forcing the coolant liner, throat support sections, and structural jacket into contact;
- heating the combustion chamber assembly to a bonding temperature for bonding the assembled parts to each other to form the combustion chamber while pressurizing the pressure furnace.
7 more elements
Dependencies are inferred from the claim text.