Fluid Flow and Dump Gap Optimization of A Aero Gas Combustor Model Using Experimental Hydraulic Analogy

For successful designing of a Aero Gas Turbine combustor, it is essential to have a detailed knowledge of the flow pattern that would exists inside the combustor and flame tube under different operating conditions. Experiments were performed on equivalent two-dimensional axisymmetric combustor model[1] using hydraulic analogy[2–4]. Inlet Fraude number in the range of 0.04 to 0.22 is used which is analogous to the actual Mach number in the axisymmetric combustor geometry. Flow visualization was performed to ascertain the extent of applicability of hydraulic analogy for investigation in such complex combustor geometry. Studies were performed to record variation in the static pressure at different locations/section in the combustor. It was also found that to optimize the overall pressure loss, the design should have provision for adjustment of dump-gap in the range of 1mm to 2mm depending on the need based on its operating Mach number.