Patent ID: 6530222
Filing Date: 2003-03-11
Classification: F23D,F23R

Abstract:
A mixer for a gas turbine combustor comprising:an annular chamber having an upstream end and a downstream end and including an annular inner wall and an annular outer wall to define the chamber, the annular inner wall extending downstream-wise, radially and outwardly, and the annular outer wall extending downstream-wise, radially and inwardly; a manifold ring closing the upstream end of the annular chamber, the manifold ring including a fuel passage in fluid communication with the annular chamber for feeding fuel into the annular chamber and a plurality of swirled air passages to provide swirled compressor air flows into the annular chamber, the swirled air flows mixing with fuel from the fuel passages, thereby producing a fuel/air mixture in the annular chamber; and a downstream end of the annular chamber being adapted to be connected to the combustor in fluid communication therewith for dumping the fuel/air mixture into the combustor for combustion.