Method of fabricating a rocket engine combustion chamber

US5249357A · kind A · utility

Assignee

• The United States of America as represented by the Administrator of the National Aeronautics and Space Administration · US

Inventors

• Richard R. Holmes · Guntersville, US
• Timothy N. McKechnie · Gurley, US
• Christopher Power · Jena, DE
• Ronald Daniel · Caterham, GB
• Robert M. Saxelby · Santa Susana, US

Key dates

• Filing date: Jan 27, 1993
• Grant date: Oct 5, 1993
• Expiry date: Jan 27, 2013

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y10T29/49346
• WIPO field: Surface technology, coating
• WIPO sector: Chemistry

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.