Strut/cavity configuration of supersonic combustor is widely employed in a scramjet engine because of its outstanding flame-holding ability, and multi-staged injection is usually collocated with strut/cavity configuration to enhance mixing with fuel and incoming flow. A numerical method is used to further investigate and optimize the performance of a strut/cavity configuration with kerosene fuel in a supersonic combustor. By altering the mass flow rate of fuel coming from the strut and wall, an agreement is reached between experimental and numerical simulation which implies that multiple-staged injection of kerosene is better than single-staged injection, and wall injection is essential for the improvement of performance. In addition, the optimization of fuel allocation and different strut positions is discussed, by comparing different allocations and locations of strut, at equally divided equivalence ratios and over 346mm from isolator entrance to achieve the highest thrust increment of a combustor.
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