Patent ID: 8381532

Claim:
A system for modifying static pressure recovery and emissions formation within a gas turbine, the system comprising: a bled diffuser positioned downstream from a compressor section of the gas turbine, said bled diffuser configured to diffuse a pressurized airflow flowing from said compressor section; a secondary combustion system located downstream from a main combustion system in a combustor, said secondary combustion system comprising at least one fuel injector configured to receive and discharge fuel from a fuel source, said at least one fuel injector being disposed downstream of a fuel nozzle assembly of said main combustion system; a bleed duct extending from said bled diffuser to said secondary combustion system, said bleed duct configured to direct bleed air from said pressurized airflow to said secondary combustion system; and wherein said bleed air flowing into said secondary combustion system is mixed with the fuel discharged from said at least one fuel injector to form an air/fuel mixture wherein said air/fuel mixture flows through a channel and into said secondary combustion system.