Granted Patent
B2
US 12,188,407 · App. 18/108,270 · Granted Jan 7, 2025
Gas turbine engine bearing and gearbox arrangement
Assignee:
RTX CORPORATION
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Abstract
A gas turbine engine includes a propulsor and a drive gear system. The drive gear system includes at least one ring gear, a plurality of intermediate gears positioned between and enmeshing with a sun gear and the at least one ring gear, with the plurality of intermediate gears carried by a gear carrier. A first bearing is configured to rotate with the gear carrier. A second bearing is on an opposite side of the drive gear system from the first bearing.
Claims (55)
1. A gas turbine engine comprising:
a propulsor delivering air into a core engine, wherein the propulsor is a fan delivering air into a bypass duct;
a drive gear system including a gear carrier and at least one ring gear, wherein the at least one ring gear is coupled to an engine case of the gas turbine engine with a compliant flexure; and
a drive shaft coupling the gear carrier in the drive gear system to the fan;
wherein a first bearing is forward of the drive gear system for supporting the drive gear system, and a second bearing is aft of the drive gear system for supporting the drive gear system;
wherein the drive gear system includes the at least one ring gear encircling a sun gear, and includes a plurality of intermediate gears positioned between and enmeshing with the sun gear and the at least one ring gear, with the plurality of intermediate gears carried by the gear carrier;
wherein the first bearing includes an inner race configured to rotate with the gear carrier and the second bearing includes an inner race configured to rotate with the gear carrier; and
wherein the second bearing supports the drive shaft relative to a rear support of a static structure, the rear support extending inward from a forward frame of the static structure behind the drive gear system relative to a longitudinal axis of the core engine.
2. The engine as recited in claim 1 , wherein one of the first and second bearings is a thrust bearing and the other of the first and second bearings is a non-thrust bearing.
3. The engine as recited in claim 2 , further comprising a low spool with a low pressure turbine, wherein the first and second bearings prevent radial excursions and overturning moments produced by the fan during operation, the low pressure turbine has three or more stages, and the drive gear system defines a speed reduction ratio between 2:1 and 13:1.
4. The engine as recited in claim 3 , wherein the first bearing is a thrust bearing, and the second bearing being a roller bearing.
5. The engine as recited in claim 1 , further comprising a low spool having a low pressure turbine and a low pressure shaft and the drive gear system includes the sun gear, wherein the low pressure turbine has three or more stages, and the drive gear system defines a speed reduction ratio between 2:1 and 13:1.
6. The engine as recited in claim 5 , wherein the low pressure shaft has a flexible forward portion.
7. The engine as recited in claim 6 , further comprising a high spool with a high pressure turbine and a high pressure shaft, wherein the low pressure shaft has a splined outer diameter surface and the sun gear has a splined inner diameter surface, the splined outer diameter surface of the low pressure shaft is interfitting with the splined inner diameter surface of the sun gear, the high pressure turbine has two stages, and the first bearing is a bidirectional tapered roller bearing.
8. The engine as recited in claim 1 , wherein the fan has a plurality of fan blades.
9. The engine as recited in claim 1 , further comprising a low pressure turbine with three or more stages, wherein the fan is a single-stage fan and the drive gear system defines a speed reduction ratio between 2:1 and 13:1.
10. The engine as recited in claim 9 , further comprising a low spool having a low pressure turbine and a low pressure shaft and the drive gear system includes the sun gear, a third bearing engaging the low pressure shaft and the drive shaft.
11. The engine as recited in claim 10 , wherein the low pressure shaft has a flexible forward portion.
12. The engine as recited in claim 11 , wherein each of the first bearing and the third bearing is a thrust bearing, and the third bearing is nested within the second bearing relative to the longitudinal axis.
13. The engine as recited in claim 10 , wherein the drive shaft is mounted to rotate with the gear carrier as a unit, and the unit engages the first bearing forward of the gear carrier and engages the second bearing aft of the gear carrier.
14. The engine as recited in claim 13 , further comprising:
a high spool with a high pressure turbine and a high pressure shaft; and
a fourth bearing engaging the low pressure shaft and a fixed frame, the fixed frame extending across a core flow path of the core engine, and the fixed frame aft of the high pressure turbine with respect to the longitudinal axis of the core engine;
wherein the high pressure turbine has two stages.
15. The engine as recited in claim 10 , wherein a centerplane of the third bearing is behind a centerplane of the second bearing by a distance no more than 10% of a radius of the second bearing with respect to the longitudinal axis of the core engine.
16. A gas turbine engine comprising:
a propulsor, wherein the propulsor is a single-stage fan;
a drive gear system including a sun gear encircled by at least one ring gear, a plurality of intermediate gears positioned between and enmeshing with the sun gear and the at least one ring gear, with the plurality of intermediate gears carried by a gear carrier;
a case with the drive gear system coupled to the case via a compliant flexure;
a drive shaft coupling the drive gear system to the fan;
a low spool extending along a longitudinal axis, the low spool including a low pressure turbine driving the drive gear system through a low shaft and the low shaft has a flexible forward portion;
a core spool including a high pressure turbine driving a high pressure compressor through a core shaft;
a first bearing configured to rotate with the gear carrier;
a second bearing located on an opposite axial side of the drive gear system from the first bearing; and
a third bearing engaging the low shaft and the drive shaft;
wherein the drive shaft is mounted to rotate with the gear carrier as a unit, the unit engages the first bearing axially forward of the gear carrier and engages the second bearing axially aft of the gear carrier with respect to the longitudinal axis, the low pressure turbine has three or more stages, the high pressure turbine has two stages, and the drive gear system defines a speed reduction ratio between 2:1 and 13:1.
17. The engine as recited in claim 16 , wherein the fan has a plurality of fan blades.
18. The engine as recited in claim 17 , wherein the fan delivers a bypass airflow into a bypass duct.
19. The engine as recited in claim 16 , wherein the unit engages the first bearing axially forward of the gear carrier and engages the second bearing axially aft of the gear carrier with respect to the longitudinal axis, and the low shaft engages the third bearing, and also engages two additional bearings axially aft of the third bearing with respect to the longitudinal axis.
20. The engine as recited in claim 19 , wherein the first bearing is a tapered roller bearing oriented to resist at least forward movement of the drive shaft with respect to the longitudinal axis, and the third bearing is a thrust bearing.
21. The engine as recited in claim 20 , wherein:
the third bearing is nested within the second bearing with respect to the longitudinal axis.
22. The engine as recited in claim 16 , further comprising:
a fourth bearing engaging the low shaft and a fixed frame;
a fifth bearing engaging the core shaft and the case; and
a sixth bearing engaging the core shaft and the case;
wherein the second bearing is a roller bearing.
23. The engine as recited in claim 22 , wherein:
the low shaft includes a spline connection to the sun gear;
the third bearing is a thrust bearing;
the fourth bearing is a roller bearing;
the fifth bearing is a thrust bearing; and
the fixed frame is axially aft of the low pressure turbine with respect to the longitudinal axis.
24. The engine as recited in claim 23 , wherein:
a centerplane of the third bearing is behind a centerplane of the second bearing by a distance no more than 10% of a radius of the second bearing with respect to the longitudinal axis.
Assignments (1)
CHANGE OF NAME
Recorded Jul 27, 2023
From: RAYTHEON TECHNOLOGIES CORPORATION
To: RTX CORPORATION
Reel/Frame 064402/0837 →
Continuity (5)
Provisional Application
61789193
· Mar 15, 2013
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