Paper Key : IRJ************622
Author: Chandra Shekhar Verma,Shailendra Kumar Bohidar
Date Published: 15 Apr 2024
Abstract
Afterburner is an additional component of Turbojet engine employed in military aircrafts to provide an increasing thrust during transonic flight, takeoff and combat situations. Afterburning is achieved by injecting additional fuel in to the jet pipe downstream of the turbine. The subsonic flow coming out from the low pressure turbine is decelerated in the diffuser to provide a velocity low enough for satisfactory combustion. The diffuser is fitted with radial airfoil struts which deswirl the flow. The presence of Diffuser struts, Fuel injection rings, Flame holders makes the flow in the after burner more complex. The detailed study of flow is required for the design and performance evaluation of the after burner.In this work the hot flow in the conceptual afterburner diffuser duct fitted with NACA 0012 airfoil struts is analyzed using Computational Fluid Dynamics method. Further CFD analysis is carried out for the diffuser duct incorporated with NACA 0012 Airfoil struts and the behavior of the flow due to the presence of airfoil struts is analyzed. The swirl angle of the flow at the exit section of the diffuser, pressure loss due to the presence of airfoil struts is studied with CFD analysis results.