Rocket nozzle system
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorsHarold A. Krayenbuhl, Gene Dolgonas, Charles J. Rogers
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Abstract
An improved rocket nozzle system having a closure insulator located adjacent the combustion chamber of a rocket engine. The closure insulator has formed as an integral part thereof a plurality of nozzles. Each of the nozzles has incorporated therein a throat insert of pyrolized graphite cloth laminate and a consumable washer. The entire closure insulator assembly including nozzles is transfer molded as one piece into a steel housing. The housing is mounted on the combustion chamber thereby providing an effective nozzle system which is reliably operable under high temperature operation.
Claims2
A rocket nozzle system comprising a supporting structure, said supporting structure having at least one nozzle formed as an integral part thereof, said nozzle having an entrance section and an exit section, a throat located intermediate said entrance and exit sections of said nozzle, a throat insert formed of a pyrolized graphite cloth laminate secured within said throat section of said nozzle, a washer of predetermined thickness being located between said throat insert and said entrance section of said nozzle, said washer being consumable at temperatures greater than approximately 700.degree. F. and yet capable of withstanding a temperature of approximately 320.degree. F. and a pressure of approximately 7000 psi with a resultant maximum reduction of said predetermined thickness of approximately 15 percent and a steel housing encompassing said supporting structure, said supporting structure being transfer molded as one piece into said steel housing.
Dependencies are inferred from the claim text.