초록 ▼

A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling tu

A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.

대표청구항 ▼

1. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section including a low pressure compressor section;a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor secti

1. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section including a low pressure compressor section;a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor section forward of said combustor section to receive a core flow along a core flow path;an intercooling turbine section rotatable about said engine axis and situated in flow communication with, and situated axially between, said low pressure compressor section and said high pressure compressor section; andan intercooling turbine section bypass to selectively bypass at least a portion of said core flow through an intercooling turbine section bypass path around said intercooling turbine section. 2. The gas turbine engine as recited in claim 1, wherein said intercooling turbine section is rotationally coupled to drive said high spool. 3. The gas turbine engine as recited in claim 1, wherein said core flow path is in communication with said combustor section. 4. The gas turbine engine as recited in claim 3, wherein said high pressure compressor section and said high pressure turbine section are in communication with said core flow path. 5. The gas turbine engine as recited in claim 1, 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. 6. The gas turbine engine as recited in claim 1, wherein said intercooling turbine section includes an intercooling turbine section inlet receiving flow from a low pressure compressor section outlet of said low pressure compressor section, and said intercooling turbine section includes an intercooling turbine section exit discharging flow to a high pressure compressor section inlet of said high pressure compressor section. 7. The gas turbine engine as recited in claim 6, wherein said intercooling turbine section includes upstream ICT variable vanes, downstream ICT variable vanes and an ICT rotor axially there between. 8. The gas turbine engine as recited in claim 1, wherein said intercooling turbine section is in a flow path that extends around said engine axis, with a split at an exit of said flow path downstream of said intercooling turbine section, said split dividing said flow path into said intercooling turbine section bypass path and said core flow path. 9. The gas turbine engine as recited in claim 8, wherein said intercooling turbine section bypass path is radially intermediate of said core flow path and a bypass flow path from said fan section. 10. A gas turbine engine comprising: a combustor section;a low spool along an engine axis with a fan section;a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor section forward of said combustor section to receive a core flow along a core flow path;an intercooling turbine section forward of said combustor section; andan intercooling turbine section bypass to selectively bypass at least a portion of said core flow through an intercooling turbine section bypass path around said intercooling turbine section, wherein said intercooling turbine section is rotationally coupled to drive said low spool. 11. A gas turbine engine comprising: a combustor section; a low spool along an engine axis with a fan section;a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor section forward of said combustor section to receive a core flow along a core flow path;an intercooling turbine section forward of said combustor section; andan intercooling turbine section bypass to selectively bypass at least a portion of said core flow through an intercooling turbine section bypass path around said intercooling turbine section, wherein said intercooling turbine section includes upstream ICT variable vanes, downstream ICT variable vanes and an ICT rotor axially therebetween. 12. The gas turbine engine as recited in claim 11, wherein said upstream intercooling turbine vanes include an inlet in communication with said core path. 13. The gas turbine engine as recited in claim 12, wherein said downstream intercooling turbine variable vanes includes an exit in communication with said core path. 14. The gas turbine engine as recited in claim 11, wherein said upstream intercooling turbine vanes are downstream of a split between said core flow path and said intercooling turbine section bypass. 15. The gas turbine engine as recited in claim 11, further comprising: a low pressure turbine (LPT) comprising LPT blades; anda high pressure turbine (HPT) comprising HPT blades,wherein the shape of at least one of the upstream ICT blades and the downstream ICT blades are similar to the shape of at least one of the LPT blades and the HPT blades. 16. A gas turbine engine comprising: a flow path extending around a central axis and having an exit;an intercooling turbine section in said flow path and rotationally coupled to at least partially drive one of a low spool and a high spool; anda split at said exit downstream of said intercooling turbine section, said split dividing said flow path into a core flow path and an intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around said intercooling turbine section. 17. The gas turbine engine as recited in claim 16, wherein said low spool includes a fan section, said fan section includes a bypass fan driven by said low spool through a geared architecture. 18. The gas turbine engine as recited in claim 16, wherein said high spool includes a high pressure compressor section and a high pressure turbine section, said high pressure compressor section is aft of said intercooling turbine section and forward of a combustor section. 19. A method of operating a gas turbine engine comprising: bypassing at least a portion of a core flow through an intercooling turbine section bypass path around an intercooling turbine section, the intercooling turbine section rotatable about an engine axis and situated in flow communication with, and situated axially between, a low pressure compressor section and a high pressure compressor section. 20. The method as recited in claim 19, further comprising: injecting the portion of the core flow through the intercooling turbine section bypass path downstream of an intercooling turbine section rotor. 21. The method as recited in claim 19, further comprising: axially injecting the portion of the core flow through the intercooling turbine section bypass path into a core flow path. 22. The method as recited in claim 19, further comprising driving the high spool with the intercooling turbine section. 23. A method of operating a gas turbine engine comprising: bypassing at least a portion of a core flow through an intercooling turbine section bypass path around an intercooling turbine section, the intercooling turbine section forward of a high pressure compressor section; andinjecting the portion of the core flow through the intercooling turbine section bypass path upstream of downstream intercooling turbine variable vanes. 24. A method of operating a gas turbine engine comprising: bypassing at least a portion of a core flow through an intercooling turbine section bypass path around an intercooling turbine section, the intercooling turbine section forward of a high pressure compressor section; andradially injecting the portion of the core flow through the intercooling turbine section bypass path into a core flow path. 25. A method of operating a gas turbine engine comprising: bypassing at least a portion of a core flow through an intercooling turbine section bypass path around an intercooling turbine section, the intercooling turbine section forward of a high pressure compressor section; andmodulating a guide vane of the intercooling turbine section to reduce an intercooling turbine expansion pressure ratio (ICT PR) during a first flight condition; andmodulating the guide vane of the intercooling turbine section to increase the intercooling turbine expansion pressure ratio (ICT PR) during a second flight condition. 26. A method of operating a gas turbine engine comprising: bypassing at least a portion of a core flow through an intercooling turbine section bypass path around an intercooling turbine section, the intercooling turbine section forward of a high pressure compressor section; anddriving the low spool with the intercooling turbine section.