Patent ID: 6442931
Filing Date: 2002-09-03
Classification: F02K

Abstract:
A combustion chamber casing of a liquid-fuel rocket engine comprisinga combustion chamber; a nozzle having a subsonic section, a supersonic section, and a throat diameter; said combustion chamber and nozzle comprising an external structural envelope and an internal fire wall which is arranged inside said external structural envelope and made from copper or a copper alloy; and a regenerative cooling passage formed between said external structural envelope and said internal fire wall; said internal fire wall having an inner surface provided with a metal coating of nickel only from 50 &mgr;m to 1000 &mgr;m thick, a layer of chromium from 10 &mgr;m to 500 &mgr;m thick being applied onto said nickel layer in a region of said nozzle throat, said region including said subsonic and supersonic sections.