Geared differential speed counter-rotatable low pressure turbine
A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.
1. A gas turbine engine counter-rotatable low pressure turbine comprising:
counter-rotatable annular outer and inner drum rotors,
the outer drum rotor rotatably connected to a low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the annular low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through an epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
2. A low pressure turbine as claimed in claim 1 , further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
3. A low pressure turbine as claimed in claim 2 , further comprising the gearbox being located aft of the outer and inner drum rotors.
4. A low pressure turbine as claimed in claim 3 , further comprising the gearbox having planetary gears rotatably mounted on pins supported by a turbine rear frame.
5. A low pressure turbine as claimed in claim 4 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
6. A low pressure turbine as claimed in claim 5 , further comprising a radially outer roller bearing disposed between the inner drum rotor and the turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
7. A low pressure turbine as claimed in claim 6 , further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
8. A low pressure turbine as claimed in claim 2 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
9. A low pressure turbine as claimed in claim 8 , further comprising the gearbox being located aft of the outer and inner drum rotors.
10. A low pressure turbine as claimed in claim 9 , further comprising a radially outer roller bearing disposed between the inner drum rotor and a turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
11. An aircraft gas turbine engine comprising:
a single stage fan section having a single fan stage having a single fan blade row,
a counter-rotatable low pressure turbine drivingly connected to the single fan stage by a low pressure shaft,
the counter-rotatable low pressure turbine including counter-rotatable annular outer and inner drum rotors,
the outer drum rotor rotatably connected to the low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through an epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
12. An engine as claimed in claim 11 , further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
13. An engine as claimed in claim 12 , further comprising the gearbox being located aft of the outer and inner drum rotors.
14. An engine as claimed in claim 13 , further comprising the gearbox having planetary gears rotatably mounted on pins supported by a turbine rear frame.
15. An engine as claimed in claim 14 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
16. An engine as claimed in claim 12 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
17. An engine as claimed in claim 16 , further comprising the gearbox being located aft of the outer and inner drum rotors.
18. An engine as claimed in claim 17 , further comprising the pins cantilevered off an annular carrier supported by a turbine rear frame.
19. An engine as claimed in claim 17 , further comprising a radially outer roller bearing disposed between the inner drum rotor and a turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
20. An engine as claimed in claim 19 , further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.
21. An aircraft gas turbine engine family comprising:
at least two different engine models having within the family having different size fans and/or operational design fan speeds and different epicyclic gearboxes with different gear ratios respectively for maintaining the same relative differential speed between outer and inner drum turbine blade rows of a counter-rotatable low pressure turbine of the different engine models;
each of the engine models includes an aircraft gas turbine engine a single stage fan section having a single fan stage having a single fan blade row and a respective one of the different size fans and/or operational design fan speeds,
the counter-rotatable low pressure turbine drivingly connected to the single fan stage by a low pressure shaft,
the outer drum rotor rotatably connected to the low pressure shaft wherein the low pressure shaft is the sole shaft operable for transmitting torque and power out of the low pressure turbine,
a plurality of axially spaced apart low pressure outer drum turbine blade rows extending radially inwardly from an outer shell of the outer drum rotor,
the low pressure inner drum rotor including a plurality of axially spaced apart low pressure inner drum turbine blade rows extending radially outwardly from the low pressure inner drum rotor,
the low pressure outer drum turbine blade rows being interdigitated with the low pressure inner drum turbine blade rows, and
the inner drum rotor being geared through the epicyclic gearbox for transmitting torque and power produced by the inner drum rotor to the low pressure shaft.
22. An engine family as claimed in claim 21 , further comprising a differential thrust bearing operably disposed between the outer and inner drum rotors.
23. An engine family as claimed in claim 22 , further comprising the gearbox being located aft of the outer and inner drum rotors.
24. An engine family as claimed in claim 23 , further comprising the gearbox having planetary gears rotatably mounted on pins supported by a turbine rear frame.
25. An engine family as claimed in claim 24 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
26. An engine family as claimed in claim 22 , further comprising:
the gearbox including a sun gear meshed with and rotatably mounted radially inwardly of the planetary gears,
a ring gear meshed with and rotatably mounted radially outwardly of the planetary gears,
the outer drum rotor being connected to the ring gear, and
the inner drum rotor being connected to the sun gear.
27. An engine family as claimed in claim 26 , further comprising the gearbox being located aft of the outer and inner drum rotors.
28. An engine family as claimed in claim 27 , further comprising the pins cantilevered off an annular carrier supported by a turbine rear frame.
29. An engine family as claimed in claim 27 , further comprising a radially outer roller bearing disposed between the inner drum rotor and a turbine rear frame and a radially inner differential roller bearing disposed between outer and inner drum rotors.
30. An engine family as claimed in claim 29 , further comprising the pins cantilevered off an annular carrier supported by the turbine rear frame.