Accession Number : AD0164885

Title :   Integral Precombustor/Ramburner Assembly.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Bradford,James N.

Report Date : 30 APR 1974

Pagination or Media Count : 4

Abstract : The patent relates to an air augmented rocket propulsion system wherein a ramburner assembly is positioned at the outlet end of a hybrid rocket gas generator. The ramburner assembly includes a bifurcated air inlet for diverting a specific portion of the ram air to a precombustor for reaction with particulate carbon admixed with the gases leaving the gas generator to produce a high temperature environment hot enough to burn the particulate carbon. The resulting heated mixture including the remaining combustibles then passes into a secondary mixing chamber where it combines with the remainder of the air from the bifurcated air inlet to be burned and momentum exchange between the gases occurs prior to exiting out the ramburner nozzle.

Descriptors :   *Ramjet engines, *Patents, Gas generator engines, Hybrid systems, Combustors, Combustion products, Burning rate

Subject Categories : Air Breathing Engines(unconventional)

Distribution Statement : APPROVED FOR PUBLIC RELEASE