Method of fabricating a rocket engine combustion chamber

Metal working – Method of mechanical manufacture – Rocket or jet device making

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427236, 427270, 427455, B23P 1500

Patent

active

052493571

ABSTRACT:
A process for making a combustion chamber for a rocket engine wherein a copper alloy in particle form is injected into a stream of heated carrier gas in plasma form which is then projected onto the inner surface of a hollow metal jacket having the configuration of a rocket engine combustion chamber. The particles are in the plasma stream for a sufficient length of time to heat the particles to a temperature such that the particles will flatten and adhere to previously deposited particles but will not spatter or vaporize. After a layer is formed, cooling channels are cut in the layer, than the channels are filled with a temporary filler and another layer of particles is deposited.

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