Rockwell International Corporation

The United States of America As Represented by the Administrator of the

Robert M Saxelby

William T Webber

Timothy N McKechnie

Richard R Holmes

Christopher A Power

Ronald L Daniel, Jr

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.

Method of fabricating a rocket engine combustion chamber

An injector assembly 10 for injecting propellants into a fluid fueled rocket engine. Injection assembly 10 comprises a plate member 12 with an opening 16 therethrough. Injector element 14 is sealed within opening 16. Oxidizer flows through central bore 18 and through orifices 26 into combustion chamber 27. Fuel flows from passageway 34 into an annular manifold 38 formed at an interface between flanged portion 32 and plate member 12. Fuel is then injected through orifices 42 into combustion chamber 27 where it impinges with the oxidizer at predetermined points in the combustion chamber 27.

Injector assembly for a fluid fueled engine

Growing community of inventors

Santa Susana, CA, United States of America

Robert M Saxelby