Patent ID: 8701383

Claim:
A gas turbine engine comprising: a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, the LLI compatible combustor being characterized as having an exit temperature exceeding 2500° F. and the first fuel having a component with a reactivity greater than that of methane; 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; and a plurality of late lean fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, wherein the fuel circuit comprises a first part that delivers the first fuel to the first interior and a second part that delivers the second fuel to the second interior, the fuel circuit connected to two different sources of fuel comprising a first source and an alternate source of fuel, the first source and alternate source of fuel each being fluidly connectable to the first part and second part of the fuel circuit, and a blend of the first and alternate sources of fuel being fluidly connectable to the first part and second part of the fuel circuit.