Abstract
In this paper, we present our main results of the firing tests of a newly proposed hydrogen fueled dual-mode scramjet combustor. The present scramjet combustor aims at obtaining a better engine performance, working characteristics and operability in wide range of flight Mach numbers. To realize such a scramjet, we especially focus on the following technical issues 1) use of parallel/low angle fuel injection, 2) control of combustor boundary layer separation, 3) good ignition/flameholding ability as well as efficient fuel/air mixing and combustion in the supersonic core flow by the streamwise vortices, and 4) selective operability of supersonic/subsonic combustion modes and efficient combustor operation in these modes. Involving these technical issues, our basic idea for the combustor of such efficient scramjet performance and operability is a multiple staged combustor characterized by the combination use of the “Alternating-Wedge strut” injector and wall-mounted ramp injectors both of which generate streamwise vortices. Firing test results showed a superior ability of this type of combustor to perform a supersonic combustion in the combustor core flow and operability in supersonic/subsonic combustion modes with high thrust performance in wide range of flight Mach numbers.
Published Version
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