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The strut based injector has been found to be one of the most promisinginjector designs for supersonic combustor, offering en-hanced mixing of fueland air. The mixing and flow field characteristics of the straight (SS) &tapered strut (TS), with fixed ramp an-gle and height at freestream Mach number2 in conjunction with fuel injection at Mach 2.3 have been investigatednumerically and reported. In the present investigation, hydrogen (H2) andethylene (C2H4) are injected in oncoming supersonic flow from the back of thestrut, where jet to freestream momentum ratio is maintained at 0.79 and 0.69for H2 & C2H4, respectively. The predicted wall static pressure and speciesmole fractions at various downstream locations are compared with theexperimental data for TS case with 0.6 mm jet diameter and found to be in goodagreement. Further, the effect of jet diameter and strut geometry on the nearfield mixing in strut ramp configuration is discussed for both the fuel. Thenumerical results are assessed based on various parameters for the performanceevaluation of different strut ramp configurations. The SS configuration forboth the injectant is found to be an optimum candidate, also it is observedthat for higher jet diameter larger combustor length is required to achievesatisfactory near field mixing.

Investigation of strut-ramp injector in a Scramjet combustor: effect of strut geometry, fuel and jet diameter on mixing characteristics