Gas turbine combustor with multiple fuel stages and method of operation

A gas turbine engine comprising:

• a compressor section;
• a turbine section;
• and
• a combustion section downstream of the compressor section and upstream of the turbine section, the combustion section comprising one or more combustors, the one or more combustors each defining a combustor axial centerline, the one or more combustors each comprising:
• a head end section defining a head end air plenum and containing a fuel nozzle assembly;
• a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein;
• a first plurality of injectors disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner, wherein at least one injector of the first plurality of injectors defines a first geometric stadium shape having first rounded ends, wherein the at least one injector of the first plurality of injectors is elongated along a first injector centerline that extends between the first rounded ends of the first geometric stadium shape, and wherein the first injector centerline is oriented at a first acute angle relative to the combustor centerline;
• a second plurality of injectors disposed at a second axial location different from the first plurality of injectors to direct a second fuel/air mixture through the liner, wherein at least one injector of the second plurality of injectors defines a second geometric stadium shape having second rounded ends, wherein the at least one injector of the second plurality of injectors is elongated along a second injector centerline that extends between the second rounded ends of the second geometric stadium shape, wherein the second injector centerline is oriented at a second acute angle relative to the combustor centerline, and wherein the first acute angle is different than the second acute angle;
• wherein each of the first plurality of injectors, the second plurality of injectors, and the head end section receives each of a first, second, and third air supply, respectively, from a compressor discharge plenum that is defined by a compressor discharge casing that at least partially surrounds the combustor, each of the first, second, and third air supply being directed to only one of the first plurality of injectors, and the second plurality of injectors, and the fuel nozzle assembly, respectively;
• and
• wherein the first plurality of injectors and the second plurality of injectors receive more than 50% of a total of the first, second, and third air supply from the compressor discharge plenum.