Experimental Investigation of a Cooling System Entrance for an Annular Gas Turbine Combustion Chamber
A cooling entrance region for a modern annular combustor has been successfully tested. Because of high heat load at the entrance part of the liner, a good design is very important. The design presented here offers ultra-low dilution, robustness and high performance. The cooling system includes convective, film and impingement techniques, which were experimentally investigated in a plastic (perspex) model of a full scale 60° sector of a simplified combustor design. The importance of a high performance entrance is obvious. It generates low pressure drop, better combustion (circumferential even flow for the liner cooling) and it gives lower flame temperature (maximizes the air in the flame). Guidelines for the design of such an entrance are presented in this paper.