Accession Number : ADD000427
Title : Step Cylinder Combustor Design.
Descriptive Note : Patent,
Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C
Personal Author(s) : Curran,Edward T
Report Date : 11 Feb 1975
Pagination or Media Count : 5
Abstract : The patent relates to a supersonic combustion ramjet having a combustor including at least two constant area combustor chamber-sections or stages disposed in open communication between the ramjet inlet and expansion nozzle. Each incorporates a combustion stabilizing step configuration and a separate fuel injector for respectively and selectively adding heat to the pair of constant area-chambers to control the heat addition to the subsonic or supersonic mode.
Descriptors : *Supersonic combustion ramjet engines, *Combustors, *Patents, Inlets, Nozzle gas flow, Fuel injectors, Combustion stability
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE