Patent ID: 7841181

Claim:
A gas turbine engine combustion system comprising: a combustion device including a combustion chamber including a primary combustion zone and a secondary combustion zone, a centerbody extending into the combustion chamber, the primary combustion zone surrounding the centerbody at a location upstream from the secondary combustion zone, a first air and fuel discharge adapted for delivering a first premixed air and fuel charge into the primary combustion zone, and a second air and fuel discharge adapted for delivering a second premixed air and fuel charge into the secondary combustion zone; wherein the first air and fuel discharge includes an annular mixing duct leading to an annular opening surrounding the centerbody and outputting to the primary combustion zone, the second air and fuel discharge includes an annular mixing duct leading to an annular opening at a downstream end of centerbody outputting to the secondary combustion zone, and a primary combustion process in the primary combustion zone is substantially completed prior to the second fuel and air discharge.