Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

Abstract

The Interstage Turbine Burner (ITB) engine provide significantly higher specific thrust with no or only small increases in thrust specific fuel consumption substitute for conventional gas engine with after-burners. Continue combustion between a high pressure turbine stage and low pressure turbine stage is organized. Ultra-Compact Combustor (UCC), which is one of mainstream design concepts of ITB, has a broad application prospect in the field of aviation with the advantages of compact structure and high combustion efficiency. In order to improve the application of Ultra-Compact Turbine interstage combustor in aero-engine, the numerical simulation was carried out by using CFD technique to research on the influence of the number of cavities in the cavity on the ITB. The results show that the increasing number of structures of cavities in the cavity will enhance the circumferential cavity of the fuel and air mixing and burning, promote the combustion mixture to the mainstream radial transport capacity and improve combustion efficiency and uniformity of exit temperature field.