NO REACTION FLOW ANALYSIS OF AERO-DERIVATIVE ANNULAR COMBUSTOR OF A TURBO-SHAFT ENGINE

Annular combustors of a generic 1100 kW class aero-derivative gas turbine are subjected to steady state incompressible cold flow analysis. The simplified computational domain is discretized with Polyhedral cells. The two equation k-Ɛ model is applied for simulati ng the turbulence with standard wall function. The Reynolds Averaged Navier-Stokes (RANS) equations are solved over the discretized domain using pressure based Semi-Implicit Method for Pressure Linked Equations (SIMPLE) and finite volume method. The calculated velocity fields at combustor exit, pressure contour, Streamlines and generation of turbulent kinetic energy on Meridional plane are presented. The aerodynamic performance resembles published annular combustor aerodynamics