Numerical Study On Strut Configuration And Strut/Cavity Integration In Supersonic Combustor

Strut injector and cavity flameholder in the scramjet was studied in this paper,the geometry configuration and injection methods of alternating-wedge strut and the combinations between strut and cavity were centered for further study using numerical simulation method.The non-reaction and reaction flow of strut with different swept configuration and alternating-wedge tail configuration was studied.It was founded that swept angle of strut can significantly reduce total pressure loss of combustor,but has a adverse effect on mixing and combustion of fuel.It can enhance streamline vorticity to facilitate fuel mixing and combusting by increasing expansion angle and compression angle of strut tail structure.Increasing side swept angle can decrease mass flow of airflow which expend along the slope of the rear strut,and then weaken the strength of the vortex flow,which has adverse effect on mixing and combusting performence of fuel.The non-reaction and reaction flow of injection angle and jet number on side wall of strut were studied.It was founded that injeting verticality is better than injecting angled,and Total pressure loss reduce with injection angle decreased.The performances of mixing and combustion in the supersonic combustor is less sensitive to injection angle.multi-hole injection not only has significantly better performance of mixing and combustion than single hole injection,but also has a more uniform distribution of flow field parameters.The arrangement of strut and cavity in supersonic combustor was studied.It was founded that low pressure in wake region of strut can make cavity shear layer tend to main flow,and can increase mass exchange rate between cavity and mainflow,when cavity was placed lengthways.The total pressure loss brougth by cavity is little.Compared to cavity placed crosswise,cavity placed lengthways has further advantageous to mixing and combustion.