초록 ▼

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a combustor section, a low spool including a fan section and an intercooling turbine section along an engine axis aft of the fan section and forward of a combustor section. The fan section a

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a combustor section, a low spool including a fan section and an intercooling turbine section along an engine axis aft of the fan section and forward of a combustor section. The fan section and the intercooling turbine section are coaxial with the low spool. A high spool along the engine axis includes a high pressure compressor section and a high pressure turbine section, the high pressure compressor section is aft of the intercooling turbine section and forward of the combustor section, and the high pressure turbine section is aft of the combustor section. The high pressure compressor section and the high pressure turbine section are coaxial with the high spool. A method of operating a gas turbine engine is also disclosed.

대표청구항 ▼

1. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section and an intercooling turbine section forward of said combustor section, said fan section and said intercooling turbine section coaxial with said low spool;a high spool along said engine axis wi

1. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section and an intercooling turbine section forward of said combustor section, said fan section and said intercooling turbine section coaxial with said low spool;a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor section and said high pressure turbine section coaxial with said high spool, said high pressure compressor section aft of said intercooling turbine section and forward of said combustor section, said high pressure turbine section aft of said combustor section; andwherein said intercooling turbine section is configured to expand flow between said fan section and an inlet of said high pressure compressor section. 2. The gas turbine engine as recited in claim 1, wherein said fan section includes a bypass fan driven by said low spool through a geared architecture. 3. The gas turbine engine as recited in claim 1, wherein said inlet of said high pressure compressor section is immediately downstream of an exit of said intercooling turbine section. 4. The gas turbine engine as recited in claim 1, wherein said high pressure turbine section is upstream of a low pressure turbine section. 5. The gas turbine engine as recited in claim 4, wherein intercooling turbine section is configured to drive a low pressure compressor section through a low shaft, and said high pressure turbine section is configured to drive said high pressure compressor section through a high shaft. 6. The gas turbine engine as recited in claim 5, wherein said intercooling turbine section is configured to expand flow between an exit of said low pressure compressor section and said inlet of said high pressure compressor section. 7. The gas turbine engine as recited in claim 5, wherein said intercooling turbine section is configured to modulate flow in a duct such that an expansion pressure ratio across intercooling turbine section is reduced during a first flight condition, and is increased during a second flight condition. 8. The gas turbine engine as recited in claim 1, wherein said intercooling turbine section includes at least an intercooling turbine vane, and at least an intercooling turbine rotor. 9. The gas turbine engine as recited in claim 8, wherein said at least an intercooling turbine vane is a variable vane. 10. The gas turbine engine as recited in claim 1, wherein said intercooling turbine section includes an upstream intercooling turbine variable vane, an intercooling turbine rotor and a downstream intercooling turbine variable vane. 11. The gas turbine engine as recited in claim 10, wherein said intercooling turbine section is configured to selectively modulate flow from said fan section to said high pressure compressor section. 12. The gas turbine engine as recited in claim 10, wherein said downstream intercooling turbine variable vane is immediately upstream of a split between a second stream bypass flow path and a core flow path. 13. The gas turbine engine as recited in claim 12, wherein said combustor section is in communication with said core flow path. 14. The gas turbine engine as recited in claim 12, wherein said high pressure compressor section and said high pressure turbine section in communication with said core flow path. 15. The gas turbine engine as recited in claim 14, further comprising an inlet guide vane upstream of said high pressure compressor section and downstream of said intercooling turbine section, said inlet guide vane within said core flow path. 16. The gas turbine engine as recited in claim 1, wherein an inlet of said intercooling turbine section is downstream from said fan section and two stages of a low pressure compressor section, and an outlet of said intercooling turbine section is upstream from each stage of said high pressure compressor section. 17. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section forward of said combustor section, said fan section coaxial with said low spool;a high spool along said engine axis with an intercooling turbine section, a high pressure compressor section and a high pressure turbine section, said intercooling turbine section and said high pressure compressor section forward of said combustor section and said high pressure turbine section aft of said combustor section, said high pressure compressor and said high pressure turbine coaxial with said high spool, said intercooling turbine section coaxial with said high spool; andwherein said intercooling turbine section is configured to expand flow between said fan section and an inlet of said high pressure compressor section. 18. The gas turbine engine as recited in claim 17, wherein said low spool includes a low pressure compressor section aft of said intercooling turbine section and forward of said combustor section. 19. The gas turbine engine as recited in claim 17, wherein said low spool includes a low pressure turbine section aft of said combustor section. 20. The gas turbine engine as recited in claim 17, wherein said fan section includes a bypass fan driven by said low spool through a geared architecture.