US 2002/0053197 A1Published application

Combustion chamber casing of a liquid-fuel rocket engine

AssigneeOtkrytoe Aktsionernoe Obschestvo

InventorsALEXANDER ALEXANDROVICH VASIN, FEDOROV VLADIMIR VLADAMIROVICH, BARAEVA GALINA ANDREEVNA

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Abstract

The casing comprises a combustion chamber and a nozzle, consisting of a subsonic and a supersonic sections with an external structural envelope and a fire wall having a ribbed external surface. The regenerative cooling passage is formed between the envelope and the fire wall. The fire wall is made from copper or a copper alloy, and the external structural envelope is made from steel or a nickel alloy. The fire wall has a metal coating stratified in the region of the nozzle throat over a length of not less than 0.3 diameter of the nozzle throat in the longitudinal direction. The first layer of the coating is nickel 50 μm to 1000 μm thick, and the second layer is chromium 10 μm to 500 μm thick.

Claims3

Dependent claims

A combustion chamber casing of a liquid-fuel rocket engine comprising a combustion chamber;

a nozzle, consisting of a subsonic and a supersonic sections with an external structural envelope and an internal fire wall arranged inside said structural envelope and made from copper or a copper alloy;
and a regenerative cooling passage formed between said structural envelope and said internal fire wall, the inner surface of said internal fire wall being provided with a metal coating consisting of two layers and arranged between the subsonic and supersonic sections of the nozzle in the region of its throat over a length of not less than 0.3 throat diameter in the longitudinal direction, the first layer of said coating being of nickel 50 μm to 1000 μm thick, and the second layer of said coating located on the nickel layer being of chromium 10 μm to 500 μm thick.

Dependencies are inferred from the claim text.