A numerical study was undertaken using the commercial computational-fluid-dynamics code to analyze the combustion behavior of a three-dimensional nonuniform-compression scramjet. Work here was inspired by Ferri’s concept of thermal compression and extended this to include the influence of three-dimensional viscous flow phenomena on the combustion behavior. A premixed mixture with an equivalence ratio of 1 was used to eliminate the influence of the fuel-injection method on the combustion characteristics. The freestream properties corresponded to a Mach 10 flight condition that gave a flow enthalpy, total temperature, and total pressure of , 4676 K, and 29 MPa, respectively. The combustion flame was found to propagate throughout the entire bottom wall of the combustor. Three flame propagation processes were identified: three-dimensional flow structures that provide ignition sources within the boundary layer, radical transport within a three-dimensional shock-induced boundary-layer separation, and thermal compression due to combustion within the high compression region. The investigation successfully characterises each individual flame propagation mechanism on the flowfield. The results highlight the closely coupled interaction between the fluid dynamic and combustion processes within a three-dimensional scramjet engine, which offers insight into how these mechanisms can be exploited to provide superior scramjet performance over a range of flight Mach numbers.
Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine
AIAA Journal ; 52 , 8 ; 1670-1685
2014-04-23
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
SUPERSONIC COMBUSTION PROCESSES IN A PREMIXED 3D NON-UNIFORM-COMPRESSION SCRAMJET ENGINE
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|Supersonic Combustion and Gasdynamics of Scramjet
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