A gas turbine engine (10) is provided and includes a combustor (20) having a first interior (21) in which a first fuel supplied thereto by a fuel circuit (70) is combustible, a turbine (50), a transition zone (43), including a second interior (41) in which a second fuel supplied thereto by the fuel circuit (70) and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors (60), which are structurally supported by the transition zone (43) and coupled to the fuel circuit (70), and which are configured to supply the second fuel to the second interior (41) in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit (70) and configured to control relative amounts of the first and second fuels supplied by the fuel circuit (70) to the first and second interiors (21, 41).
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