Patent ID: 8112216

Claim:
A gas turbine engine comprising: a combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible; a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power the rotation of the turbine blades; a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another; a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages; a compressor, fluidly coupled to the combustor and the transition zone, by which air is supplied to the first and second interiors for the combustion therein; and a control system coupled to the fuel circuit and configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.