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Abstract
Further experimental results are described from the multi-annular swirl burner (MASB). The burner comprises a plurality of concentric annular divergent nozzles with the inner end of each nozzle aligned substantially with the outer end of the adjacent nozzle. The MASB makes use of the principle that under turbulent conditions high volumetric heat release rates can be achieved by matching the concentrations and directions of flow of reactants in such a way that regions of high fuel concentration overlap regions of large shear stresses in the flow. Wider stability limits and better mixing of reactants are found in this MASB compared to the conventional type of single annular swirl burner.
Laser anemometry system was used to obtain the three components of mean and r.m.s. velocity together with the higher moments of turbulence. Results were obtained under non-combustive and combustive conditions both with and without extension tube attached to the burner exit. The results indicate clearly an increase in both mean and r.m.s. velocity with combustion.
An extension tube having 25 percent restriction at one end was attached to the burner exit for demonstrating the burner application as a small gas turbine combustor. Results show a far more uniform distribution of the mean temperatures coupled with complete burn out by the combustor exit. The combustor has been demonstrated to be beneficial in alleviating film cooling problems in a gas turbine combustor.
Pressure loss coefficient from this burner was found to be of the same order of magnitude as that obtained from conventional type of single annular swirl burners