Abstract:In gas turbines, combustor inlets are characterised by significant levels of unsteady circumferential distortion due to compressor wakes and secondary flows, together with additional radial non-uniformity induced by the adverse pressure gradients in the pre-diffuser. This can cause non-uniform velocity distributions across the fuel injector, although the exact interaction mechanism, and the effects it has on the downstream air-fuel mixing, is not fully understood. This paper investigates the flow in an a singl… Show more
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