Analysis of non-reacting flow in an aircraft gas turbine engine afterburner model using finite volume method

This paper focuses on the aerodynamics of the non-reacting flow inside an aero-gas turbine engine afterburner by carrying out a three-dimensional CFD analysis using the finite volume approach. A 60° sector of the afterburner with all the complexities has been modelled to take advantage of the symmetry of the design. The computational methodology employed SIMPLE algorithm for pressure velocity coupling, RNG k-ε model for turbulence in an unstructured and non-uniform grid. The analysis has been carried out for sea level inlet conditions. A recirculation zone was seen to be formed behind the V-gutters and inner wall of the diffuser. The performance of the diffuser was found to be good and the Mach number just upstream of the V-gutter was found to be in line with requirements. The pressure loss was in line with successful designs and the nozzle performance was found to be satisfactory. The predicted flow fields are verified using existing experimental results. The results for various mass flow rates and different geometries are presented for the closed nozzle position.