초록 ▼

An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant system which includes a manifold fo

An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant system which includes a manifold formed from a non-copper material through which a coolant flows. In a high heat transfer embodiment, the transition zone includes an additional manifold formed from a copper based material.

대표청구항 ▼

What is claimed is: 1. A method of assembling a rocket engine having a combustion chamber, a smooth wall nozzle, and a coolant system with a transition zone between said combustion chamber and said nozzle, the method comprising the steps of: forming the transition zone by providing a first manifold

What is claimed is: 1. A method of assembling a rocket engine having a combustion chamber, a smooth wall nozzle, and a coolant system with a transition zone between said combustion chamber and said nozzle, the method comprising the steps of: forming the transition zone by providing a first manifold having a plurality of holes and a plurality of grooves cut between adjacent ones of said holes for transitioning from gullies between external surfaces of said holes to a flat wall profile; inserting braze performs into said holes; inserting a plurality of tube assemblies into the holes; and furnace brazing the tube assemblies to the first manifold. 2. A method according to claim 1, wherein said providing step comprises providing a first manifold formed from a non-copper material. 3. A method according to claim 1, wherein said providing step comprises providing a second manifold formed from a non-copper material and providing a first manifold formed from a copper based material and joining said first manifold to said second manifold. 4. A method according to claim 1, further comprising welding said nozzle on said first manifold. 5. A method according to claim 1, further comprising joining said combustion chamber to said coolant system. 6. A method for assembling a rocket engine having a combustion chamber, a smooth wall nozzle, and a coolant system with a transition zone between said combustion chamber and said nozzle, the method comprising the steps of: forming the transition zone by providing a first manifold having a first set of holes and a second manifold having a second set of holes; aligning said first manifold relative to said second manifold so that said first set of holes are aligned with said second set of holes; inserting braze preforms into said first and second set of holes; providing a plurality of tube assemblies with each of said tube assemblies having an internal ferrule with a free end; inserting each said internal ferrule into a respective one of said first holes so that said internal ferrule passes through said first manifold and into a respective one of said second holes so that said free end terminates in said second manifold; and brazing said internal ferrule to said first and second manifolds by melting said braze preforms. 7. The method according to claim 6, wherein said first and second manifold providing step comprises providing a first manifold formed from a copper based material and a second manifold formed from a non-copper material. 8. The method according to claim 6, wherein said second manifold providing step comprises providing a manifold formed from steel. 9. The method according to claim 6, wherein said second manifold providing step comprises providing a manifold formed from a nickel based alloy containing greater than 50% by weight nickel. 10. The method according to claim 6, wherein said tube assembly providing step comprises providing a tube assembly having a tiered configuration with a diameter near the free end being smaller than a diameter of the internal ferrule in the first manifold. 11. The method according to claim 6, further comprising welding the smooth wall nozzle to seal coolant passages. 12. The method according to claim 6, further comprising joining the combustion chamber to said coolant system.