Granted Patent
B2
US 12,385,409 · App. 18/818,804 · Granted Aug 12, 2025
Epicyclic gear train
Inventors:
Michael E. McCune (Colchester, CT); Lawrence E. Portlock (Bethany, CT); Frederick M. Schwarz (Glastonbury, CT)
Assignee:
RTX CORPORATION
F01D15/12F01D1/02F01D5/02F01D5/027F01D25/16F01D25/18F02C7/32F16H57/04F02C7/36F02K3/06F05D2220/32F05D2220/36F05D2240/70F05D2260/34F05D2260/40311F16H57/0423F16H57/0479F16H57/0486F16H2057/085
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Abstract
A gas turbine engine according to an example of the present disclosure includes a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.
Claims (56)
1. A gas turbine engine comprising:
a propulsor section including a propulsor supported on a propulsor shaft;
a turbine section including a turbine shaft;
a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis; and
an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft, the epicyclic gear train comprising:
a sun gear coupled to the turbine shaft;
intermediary gears arranged circumferentially about and meshing with the sun gear;
a carrier and support means for supporting each of the intermediate gears relative to the carrier; and
a ring gear including first and second portions, the first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears, the first and second portions having axially opposed faces abutting one another at a radial interface, the ring gear including discharge means for expelling lubricant from the radial interface outwardly of the ring gear, and the discharge means including facing recesses of the first and second portions that form an internal annular cavity along the radial interface;
wherein the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.5, and the ring gear includes engagement means for forcing the first portion and the second portion toward one another at the radial interface.
2. The gas turbine engine as recited in claim 1 , wherein the epicyclic gear train is a planetary gear system.
3. The gas turbine engine as recited in claim 1 , wherein the ring gear includes attachment means for securing the first and second portions of the ring gear to the propulsor shaft.
4. The gas turbine engine as recited in claim 1 , wherein the first and second portions of the gear train includes means for resisting overturning moments.
5. The gas turbine engine as recited in claim 1 , wherein the ring gear includes accumulation means for capturing lubrication expelled toward the radial interface.
6. The gas turbine engine as recited in claim 1 , wherein the support means includes journal bearings that support the respective intermediate gears, and each journal bearing includes lubrication means for conveying lubricant through the journal bearing to a peripheral journal surface of the journal bearing.
7. The gas turbine engine as recited in claim 1 , wherein the gear train includes a torque frame having securement means for fixing the carrier to a fixed housing.
8. The gas turbine engine as recited in claim 1 , wherein:
the gear train includes collection means for receiving lubricant expelled by the discharge means through the radial interface;
the discharge means inhibits an axial flow of lubricant passing along the radial interface prior to being expelled toward the collection means; and
the gear train includes return means for communicating lubricant from an outer periphery of the respective first and second portions of the ring gear outwardly to the collection means.
9. The gas turbine engine as recited in claim 1 , further comprising:
an input shaft that interconnects the sun gear and the turbine shaft, the input shaft including an undulation that extends radially outward relative to the engine axis.
10. The gas turbine engine as recited in claim 1 , wherein the discharge means includes grooves at the radial interface that form a hole.
11. The gas turbine engine as recited in claim 10 , wherein the hole provides a direct radial path through the ring gear.
12. The gas turbine engine as recited in claim 1 , wherein the propulsor is a turbo fan, and the propulsor shaft is a fan shaft supporting the fan.
13. A gas turbine engine comprising:
a propulsor section including a propulsor supported on a propulsor shaft;
a turbine section including a turbine shaft;
a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis; and
an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft, the epicyclic gear train comprising:
a sun gear coupled to the turbine shaft;
intermediary gears arranged circumferentially about and meshing with the sun gear;
a carrier and support means for supporting each of the intermediate gears relative to the carrier; and
a ring gear including first and second portions, the first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears, the first and second portions having axially opposed faces abutting one another at a radial interface, the ring gear including discharge means for expelling lubricant from the radial interface outwardly of the ring gear, and the discharge means including facing recesses of the first and second portions that form an internal annular cavity along the radial interface;
wherein the propulsor is a turbo fan, and the propulsor shaft is a fan shaft supporting the fan.
14. The gas turbine engine as recited in claim 13 , wherein the ring gear includes attachment means for securing the first and second portions of the ring gear to the propulsor shaft.
15. The gas turbine engine as recited in claim 13 , wherein the first and second portions of the gear train includes means for resisting overturning moments.
16. The gas turbine engine as recited in claim 13 , wherein the ring gear includes accumulation means for capturing lubrication expelled toward the radial interface.
17. The gas turbine engine as recited in claim 13 , wherein the gear train includes a torque frame having securement means for fixing the carrier to a fixed housing.
18. The gas turbine engine as recited in claim 13 , wherein:
the gear train includes collection means for receiving lubricant expelled by the discharge means through the radial interface;
the discharge means inhibits an axial flow of lubricant passing along the radial interface prior to being expelled toward the collection means; and
the gear train includes return means for communicating lubricant from an outer periphery of the respective first and second portions of the ring gear outwardly to the collection means.
19. A gas turbine engine comprising:
a propulsor section including a propulsor supported on a propulsor shaft;
a turbine section including a turbine shaft;
a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis; and
an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft, the epicyclic gear train comprising:
a sun gear coupled to the turbine shaft;
intermediary gears arranged circumferentially about and meshing with the sun gear;
a carrier and support means for supporting each of the intermediate gears relative to the carrier;
a ring gear including first and second portions, the first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears, the first and second portions having axially opposed faces abutting one another at a radial interface, the ring gear including discharge means for expelling lubricant from the radial interface outwardly of the ring gear, and the discharge means including facing recesses of the first and second portions that form an internal annular cavity along the radial interface; and
sealing means along an outer periphery of the respective first and second portions.
20. The gas turbine engine as recited in claim 19 , wherein:
the gear train includes collection means for receiving lubricant expelled by the discharge means through the radial interface;
the gear train includes return means for communicating lubricant from the outer periphery of the respective first and second portions of the ring gear outwardly to the collection means.
Continuity (10)
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