Counter-rotating low pressure turbine without turbine exhaust case
A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is engaged to the outer rotor and is positioned upstream of the inner set of blades.
1. A gas turbine engine comprising:
a shaft defining an axis of rotation;
a combustor section upstream of a turbine section and downstream of a compressor section,
the turbine section comprising:
an inner rotor directly driving the shaft, the inner rotor including an inner set of blades; and
an outer rotor having an outer set of blades interspersed with the inner set of blades, the outer rotor configured to rotate in an opposite direction about the axis of rotation from the inner rotor;
a gear system mounted to a mid-turbine frame structure and engaged to the outer rotor wherein the gear system is positioned upstream of the inner set of blades and downstream of the combustor section;
wherein the gear system includes a ring gear engaged to the outer rotor, a plurality of star gears in meshing engagement with the ring gear, and a sun gear in meshing engagement with the star gears, and wherein the star gears are supported within a carrier that is mounted to the mid-turbine frame structure; and
a first bearing positioned between the shaft and the carrier to support the shaft for rotation relative to the carrier and mid-turbine frame structure.
2. The gas turbine engine according to claim 1 , wherein the sun gear is fixed for rotation with the shaft about the axis of rotation.
3. The gas turbine engine according to claim 1 , wherein the first bearing is positioned upstream of the inner and outer sets of blades.
4. The gas turbine engine according to claim 1 , including a second bearing supporting a fore end of the outer rotor for rotation relative to the mid-turbine frame structure and a third bearing supporting an aft end of the outer rotor for rotation relative to the shaft.
5. The gas turbine engine according to claim 4 , wherein the first and second bearings are generally radially aligned with each other in an overlapping relationship.
6. The gas turbine engine according to claim 4 , wherein the first bearing is positioned upstream of the inner and outer sets of blades and is between the shaft and the carrier in a radial direction.
7. The gas turbine engine according to claim 6 , wherein the second bearing is between the outer rotor and the mid-turbine frame.
8. The gas turbine engine according to claim 1 , including a seal located at an interface between the mid-turbine frame structure and the outer rotor.
9. The gas turbine engine according to claim 1 , wherein the outer rotor comprises an aftmost end of the engine.
10. The gas turbine engine according to claim 1 , wherein a fore end of the shaft is associated with a counter-rotating low pressure compressor, and wherein the gear system comprises a first gear system and including a second gear system associated with the counter-rotating low pressure compressor that is independent of the first gear system.
11. The gas turbine engine according to claim 1 , including a seal between the mid-turbine frame structure and the outer rotor.
12. A gas turbine engine comprising:
a core air flowpath;
a shaft supporting a compressor section and a turbine section arranged within the core flowpath;
a combustor section upstream of the turbine section and downstream of the compressor section; and
wherein the turbine section includes a counter-rotating low pressure turbine comprising:
an inner rotor directly driving the shaft, the inner rotor including an inner set of blades,
an outer rotor having an outer set of blades interspersed with the inner set of blades, the outer rotor configured to rotate in an opposite direction about the axis of rotation from the inner rotor,
a gear system mounted to a mid-turbine frame structure and engaged to the outer rotor wherein the gear system is positioned upstream of the inner set of blades and downstream of the combustor section,
wherein the gear system includes a ring gear engaged to the outer rotor, a plurality of star gears in meshing engagement with the ring gear, and a sun gear in meshing engagement with the star gears, and wherein the star gears are supported within a carrier that is mounted to the mid-turbine frame structure and
a first bearing positioned between the shaft and the carrier to support the shaft for rotation relative to the carrier and mid-turbine frame structure.
13. The gas turbine engine according to claim 12 , wherein the compressor section includes a high pressure compression section that has a pressure ratio of approximately 23:1.
14. The gas turbine engine according to claim 12 , wherein the compressor section includes a counter-rotating low pressure compressor driven by the shaft, wherein the gear system comprises a first gear system and including a second gear system associated with the counter-rotating low pressure compressor that is independent of the first gear system.
15. The gas turbine engine according to claim 12 , including a second bearing supporting a fore end of the outer rotor for rotation relative to the mid-turbine frame structure and a third bearing supporting an aft end of the outer rotor for rotation relative to the shaft, and wherein the first and second bearings are upstream of the inner and outer sets of blades.
16. The gas turbine engine according to claim 15 , wherein the first and second bearings are generally radially aligned with each other in an overlapping relationship.
17. The gas turbine engine according to claim 15 , wherein the first and second bearings are roller bearings and the third bearing is a ball bearing.
18. The gas turbine engine according to claim 15 , wherein the first bearing is between the shaft and the carrier in a radial direction.
19. The gas turbine engine according to claim 18 , wherein the second bearing is between the outer rotor and the mid-turbine frame.
20. The gas turbine engine according to claim 12 , including a seal located between the mid-turbine frame structure and the outer rotor.
21. The gas turbine engine according to claim 12 , wherein the sun gear is fixed for rotation with the shaft about the axis of rotation.
22. The gas turbine engine according to claim 12 , including a seal between the mid-turbine frame structure and the outer rotor.