초록 ▼

A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fue

A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, 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 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.

대표청구항 ▼

1. 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 h

1. 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; anda 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. 2. The gas turbine engine according to claim 1, wherein the LLI compatible combustor has an exit temperature that exceeds 2500° F. 3. The gas turbine engine according to claim 1, wherein the LLI compatible combustor is configured to combust fuels with components that are more reactive than methane. 4. The gas turbine engine according to claim 3, wherein the LLI compatible combustor is characterized by having a hot side residence time which is greater than 10 ms. 5. The gas turbine engine according to claim 1, wherein the LLI compatible combustor comprises multiple premixing nozzles to inject the first fuel, having been premixed, into the first interior. 6. The gas turbine engine according to claim 1, wherein the LLI compatible combustor comprises a Dry Low NOx (DLN) 1+ combustor. 7. The gas turbine engine according to claim 1, wherein the LLI compatible combustor comprises a Dry Low NOx (DLN) 2+ combustor. 8. The gas turbine engine according to claim 1, wherein the LLI compatible combustor comprises a Dry low NOx (DLN) 2.6/2.6+ combustor. 9. The gas turbine engine according to claim 1, wherein the LLI compatible combustor comprises a diffusion style combustor. 10. The gas turbine engine according to claim 1, wherein the second part of the fuel circuit comprises multiple branches, and wherein the fuel circuit further comprises a valve to control an amount of fuel transmittable from the first part to the multiple branches. 11. The gas turbine engine according to the claims 10, further comprising: multiple valves respectively coupled to each of multiple branches of the second part and to a supply of inlet air such that at least the second fuel and air are deliverable by each of the multiple valves into the plurality of the fuel injectors from the multiple branches, respectively. 12. The gas turbine engine according to claim 1, wherein the transition zone comprises an outer surface, the outer surface defining one or more dilution holes therethrough, and wherein one of the plurality of fuel injectors is structurally supported by one of the dilution holes in the outer surface of the transition zone. 13. The gas turbine engine according to claim 1, wherein the fuel injectors are multi-tube/showerhead injectors. 14. The gas turbine engine according to claim 1, wherein the fuel injectors are swirl injectors. 15. The gas turbine engine according to claim 1, wherein the fuel injectors are tube-in-tube injectors.