초록 ▼

A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaf

A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaft turbines with a row of low pressure variable vanes disposed therebetween and drivingly connected to coaxial low pressure inner and outer shafts respectively which are located radially inwardly of the high pressure spool. The low pressure inner and outer shaft turbines are drivingly connected to a forward and aft fan blade rows by the low pressure inner and outer shafts. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.

대표청구항 ▼

1. A gas turbine engine turbine assembly comprising:a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft and rotatable about an engine centerline,a low pressure turbine having a low pressure turbine flowpath and located af

1. A gas turbine engine turbine assembly comprising:a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft and rotatable about an engine centerline,a low pressure turbine having a low pressure turbine flowpath and located aft of said high pressure spool,said low pressure turbine having counter rotatable low pressure inner and outer shaft turbines,said low pressure turbine having low pressure inner and outer shafts respectively which are at least in part rotatably disposed coaxial with and radially inwardly of said high pressure spool,said low pressure inner shaft turbine including first low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a forward fan blade row by said low pressure inner shaft,said low pressure outer shaft turbine including second low pressure turbine blade rows disposed across said low pressure turbine flowpath and drivingly connected to a aft fan blade row by said low pressure outer shaft,a single direction of rotation booster having at least a rotatable first row of booster blades drivenly connected to said low pressure outer shaft and axially located aft and downstream of said aft fan blade row, andat least one row of low pressure variable vanes disposed across said low pressure turbine flowpath between said low pressure inner and outer shaft turbines. 2. An assembly as claimed in claim 1 further comprising a core engine inlet to said high pressure compressor and said booster being operably disposed entirely within said core engine inlet to direct substantially all booster air from said booster into said high pressure compressor. 3. An assembly as claimed in claim 2 further comprising forward and aft rows of booster vanes axially disposed forwardly and aftwardly respectively of said first row of booster blades of said booster. 4. An assembly as claimed in claim 2 further comprising a second row of booster blades and forward and aft booster vanes disposed forwardly and aftwardly of said first and second rows of booster blades of said booster respectively and at least one middle row of booster vanes axially disposed between each pair of said rows of booster blades. 5. An assembly as claimed in claim 1 further comprising at least one adjacent pair of one of said first low pressure turbine blade rows and one of said second low pressure turbine blade rows and said row of low pressure variable vanes disposed across said low pressure turbine flowpath between said adjacent pair. 6. An assembly as claimed in claim 1 further comprising:a core engine inlet to said high pressure compressor,said core engine inlet having an inlet duct splitter,said inlet duct splitter axially and radially disposed adjacent to and downstream of said booster for splitting booster air from said booster into booster air first and second portions, andsaid inlet duct splitter positioned for directing said booster air first portion into said core engine inlet and said booster air second portion around said core engine inlet. 7. An assembly as claimed in claim 6 further comprising at least one row of booster blades surrounded by a splitter shroud having a leading edge splitter, said leading edge splitter operably disposed adjacent to and downstream of said aft fan blade row for splitting fan flow air exiting said aft fan blade row into a fan flow air first portion into said booster and a fan flow air second portion around said booster. 8. An assembly as claimed in claim 7 further comprising forward and aft booster vanes disposed forwardly and aftwardly of said booster blades respectively. 9. An assembly as claimed in claim 8 further comprising said aft row of booster vanes having radially inner vane portions disposed within said core engine inlet and radially outer vane portions disposed between said splitter shroud and a core engine inlet shroud which includes said inlet duct splitter. 10. An assembly as claime d in claim 6 further comprising at least one adjacent pair of said first low pressure turbine blade rows and one of said second low pressure turbine blade rows and said row of low pressure variable vanes disposed across said low pressure turbine flowpath between said adjacent pair. 11. An assembly as claimed in claim 1 further comprising said first low pressure turbine blade rows interdigitated with said low pressure second turbine blade rows. 12. An assembly as claimed in claim 11 further comprising a core engine inlet to said high pressure compressor and said booster being operably disposed entirely within said core engine inlet to direct substantially all booster air from said booster into said high pressure compressor. 13. An assembly as claimed in claim 12 further comprising forward and aft rows of booster vanes axially disposed forwardly and aftwardly respectively of said first row of booster blades of said booster. 14. An assembly as claimed in claim 12 further comprising a second row of booster blades and forward and aft booster vanes disposed forwardly and aftwardly of said first and second rows of booster blades of said booster respectively and at least one middle row of booster vanes axially disposed between each pair of said rows of booster blades. 15. An assembly as claimed in claim 11 further comprising at least one adjacent pair of one of said first low pressure turbine blade rows and one of said second low pressure turbine blade rows and said row of low pressure variable vanes disposed across said low pressure turbine flowpath between said adjacent pair. 16. An assembly as claimed in claim 11 further comprising:a core engine inlet to said high pressure compressor,said core engine inlet having an inlet duct splitter,said inlet duct splitter axially and radially disposed adjacent to and downstream of said booster for splitting booster air from said booster into booster air first and second portions, andsaid inlet duct splitter positioned for directing said booster air first portion into said core engine inlet and said booster air second portion around said core engine inlet. 17. An assembly as claimed in claim 16 further comprising at least one row of booster blades surrounded by a splitter shroud having a leading edge splitter, said leading edge splitter operably disposed adjacent to and downstream of said aft fan blade row for splitting fan flow air exiting said aft fan blade row into a fan flow air first portion into said booster and a fan flow air second portion around said booster. 18. An assembly as claimed in claim 17 further comprising forward and aft booster vanes disposed forwardly and aftwardly of said booster blades respectively. 19. An assembly as claimed in claim 18 further comprising said aft row of booster vanes having radially inner vane portions disposed within said core engine inlet and radially outer vane portions disposed between said splitter shroud and a core engine inlet shroud which includes said inlet duct splitter. 20. An assembly as claimed in claim 19 further comprising said aft row of booster vanes having radially inner vane portions disposed within said core engine inlet and radially outer vane portions disposed between said splitter shroud and a core engine inlet shroud which includes said inlet duct splitter. 21. An assembly as claimed in claim 11 further comprising a first forwardmost row of said first low pressure turbine blade rows interdigitated with a forwardmost pair of said low pressure second turbine blade rows and said row of low pressure variable vanes disposed between a second forwardmost row of said forwardmost pair of said low pressure second turbine blade rows and said first forwardmost row of said first low pressure turbine blade rows. 22. An assembly as claimed in claim 21 further comprising a core engine inlet to said high pressure compressor and said booster being operably disposed entirely within said core engine inlet to direct substantially all booster air fro m said booster into said high pressure compressor. 23. An assembly as claimed in claim 22 further comprising forward and aft rows of booster vanes axially disposed forwardly and aftwardly respectively of said first row of booster blades of said booster. 24. An assembly as claimed in claim 22 further comprising a second row of booster blades and forward and aft booster vanes disposed forwardly and aftwardly of said first and second rows of booster blades of said booster respectively and at least one middle row of booster vanes axially disposed between each pair of said rows of booster blades. 25. An assembly as claimed in claim 11 further comprising an aftmost row of said second low pressure turbine blade rows interdigitated with an aftmost pair of the low pressure first turbine blade rows and said row of low pressure variable vanes disposed between a second aftmost row of said aftmost pair of said low pressure second turbine blade rows and said aftmost row of said second low pressure turbine blade rows. 26. An assembly as claimed in claim 25 further comprising a core engine inlet to said high pressure compressor and said booster being operably disposed entirely within said core engine inlet to direct substantially all booster air from said booster into said high pressure compressor. 27. An assembly as claimed in claim 26 further comprising forward and aft rows of booster vanes axially disposed forwardly and aftwardly respectively of said first row of booster blades of said booster. 28. An assembly as claimed in claim 26 further comprising a second row of booster blades and forward and aft booster vanes disposed forwardly and aftwardly of said first and second rows of booster blades of said booster respectively and at least one middle row of booster vanes axially disposed between each pair of said rows of booster blades. 29. An assembly as claimed in claim 1 further comprising said counter rotatable low pressure inner and outer shaft turbines being tandem non-interdigitated aft and forward low pressure turbines respectively and said row of low pressure variable vanes is axially disposed between said forward and aft low pressure turbines. 30. An assembly as claimed in claim 29 further comprising said first low pressure turbine blade rows of said aft low pressure turbines having one row of stator vanes axially disposed between each pair of said second low pressure turbine blade rows and disposed across said low pressure turbine flowpath and said second low pressure turbine blade rows of said forward low pressure turbines having one row of said stator vanes axially disposed between each pair of said first low pressure turbine blade rows and disposed across said low pressure turbine flowpath. 31. An assembly as claimed in claim 29 further comprising a core engine inlet to said high pressure compressor and said booster being operably disposed entirely within said core engine inlet to direct substantially all booster air from said booster into said high pressure compressor. 32. An assembly as claimed in claim 31 further comprising forward and aft rows of booster vanes axially disposed forwardly and aftwardly respectively of said first row of booster blades of said booster. 33. An assembly as claimed in claim 31 further comprising a second row of booster blades and forward and aft booster vanes disposed forwardly and aftwardly of said first and second rows of booster blades of said booster respectively and at least one middle row of booster vanes axially disposed between each pair of said rows of booster blades. 34. An assembly as claimed in claim 29 further comprising:a core engine inlet to said high pressure compressor,said core engine inlet having an inlet duct splitter,said inlet duct splitter axially and radially disposed adjacent to and downstream of said booster for splitting booster air from said booster into booster air first and second portions, andsaid inlet duct splitter positioned for directing said booster air first port ion into said core engine inlet and said booster air second portion around said core engine inlet. 35. An assembly as claimed in claim 34 further comprising at least one row of booster blades surrounded by a splitter shroud having a leading edge splitter, said leading edge splitter operably disposed adjacent to and downstream of said aft fan blade row for splitting fan flow air exiting said aft fan blade row into a fan flow air first portion into said booster and a fan flow air second portion around said booster. 36. An assembly as claimed in claim 35 further comprising forward and aft booster vanes disposed forwardly and aftwardly of said booster blades respectively. 37. An assembly as claimed in claim 36 further comprising said aft row of booster vanes having radially inner vane portions disposed within said core engine inlet and radially outer vane portions disposed between said splitter shroud and a core engine inlet shroud which includes said inlet duct splitter.