Flow conditions analysis of Gas Turbine Combustor

Gas turbines are equipped for working effectively on a wide assortment of energizes. Combustor is directed to a great extent by the requirement for its length and frontal territory to stay inside the cut-off points set by other motor segments by the need for a diffuser to limit pressure problems, another issue of expanding significance is that acoustic reverberation. The decrease of combustor size and weight is another significant necessity for air motors. The aim of the present work is to analyse the combustion chamber geometry using FINE/OPEN of NUMECA software and to predict the hot and cold total pressure loss, (circumferential and radial) pattern factors and combustion efficiency. This paper mainly work towards understanding the effect of cold and hot flow in a practical combustor systems using CFD and to estimate the various parameters like pressure loss, pattern factor (circumferential and radial), velocity distribution through diffuser, dome, swirler, three zones and combustor holes. The flow analysis is further extended to investigate the effects of temperature distribution of the flow that reaches the turbine inlet. The combustor model is created using CATIA and parts are then cleaned individual using CADfix suitable for meshing. The performance of the turbulence model is analysed and compared. Present work deals with the implementation of Computational Fluid Dynamics (CFD) for three-dimensional analysis of flow in an annular combustor of an aero gas turbine engine. FINE/OPEN of NUMECA commercial code will be used to analyse the Combustion chamber geometry. The analysis is carried out both in FLUENT and NUMECA and the results are compared.