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