Axially staged gas turbine combustor with interstage premixer

An axially staged combustion system comprising:

• a combustion liner having an inlet end, an outlet end, and a first combustion chamber positioned therebetween;
• a transition duct in fluid communication with the combustion liner and positioned downstream, in an axial direction, from the combustion liner;
• and
• a premixer positioned generally between the combustion liner and the transition duct in the axial direction for providing a homogeneously mixed flow of fuel and air to a second combustion stage spaced downstream, in the axial direction, from the first combustion chamber, the premixer comprising:
• an annular opening positioned radially outward of an aft end of the combustion liner and configured to receive compressed air;
• a plurality of channels spaced a distance apart and positioned downstream, in the axial direction, from the annular openino, wherein the annular opening is configured to direct the compressed air into the pluralit of channels, and wherein the pluralit of channels is configured to direct the compressed air downstream, in the axial direction, to the second combustion stage;
• and
• one or more fuel injectors positioned within one or more of the channels for injecting a flow of fuel into the channels.