Process for reducing gaseous heat transfer to the wall of the combustion chamber for a rocket apparatus

摘要

781,998. Combustion chamber linings. ANSTALT FUR DIE ENTWICKLUNG VON ERFINDUNGEN UND GEWERBLICHEN ANWENDUNGEN ENERGA. June 6. 1955 [June 10, 1954], No. 16234/55. Class 51 (1). The thermic effects of the combustion gases on the combustion chamber wall of a rocket apparatus are reduced by adding to the propelling agent, or to one of its components, a substance which at the time of gasification of the agent forms a solid deposit on the chamber wall. This lining, which when the propelling agent comprises nitric acid and the additive comprises a chromium or nickel salt comprises a precipitate in the form of nitride of chromium or nickel, enables, by its heat-insulating property, a combustion chamber wall construction of relatively inexpensive steel preferably cooled by an external water cooling device. To permit deposition of the nitride precipitate it is necessary in the operation of the rocket combustion apparatus to reduce the temperature of the combustion gases in the vicinity of the chamber wall to below that of the melting point of the chromium or nickel salts. This may be effected by supplying an excess of propelling agent or one of its components.