Granted Patent
B2
US 12,480,441 · App. 18/959,834 · Granted Nov 25, 2025
Gas turbine engine bearing and gearbox arrangement
Assignee:
RTX CORPORATION
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Abstract
A gas turbine engine includes a plurality of blades that deliver air into a compressor section and a drive gear system including an epicyclic transmission. A drive shaft interconnects a gear carrier of the epicyclic transmission and the plurality of blades. A turbine section drives an input of the drive gear system through a turbine shaft. The drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system. A ring gear of the epicyclic transmission is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing.
Claims (66)
1 . A gas turbine engine comprising:
a plurality of blades that deliver air into a compressor section;
a drive gear system including an epicyclic transmission, the epicyclic transmission including a gear carrier, a ring gear encircling a sun gear, and a plurality of intermediate gears positioned between and enmeshing with the sun gear and the ring gear, wherein the plurality of intermediate gears are carried by the gear carrier;
a drive shaft interconnecting the gear carrier and the plurality of blades; and
a turbine section that drives an input of the drive gear system through a turbine shaft;
wherein the drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system relative to an engine longitudinal axis; and
wherein the ring gear is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing relative to the engine longitudinal axis;
wherein the second bearing supports an aft portion of the drive shaft relative to a rear support of a static structure; and
the rear support extends radially inward from a forward frame of the static structure at a position that is aft of the drive gear system relative to the engine longitudinal axis.
2 . The engine as recited in claim 1 , wherein the compliant flexure is axially aligned with an outer diameter of the ring gear relative to the engine longitudinal axis.
3 . The engine as recited in claim 1 , wherein:
the turbine shaft includes a main portion and a flexible forward portion; and
the flexible forward portion interconnects the main portion of the turbine shaft and the input of the drive gear system.
4 . The engine as recited in claim 3 , wherein:
the flexible forward portion extends axially forward of the second bearing relative to the engine longitudinal axis.
5 . The engine as recited in claim 1 , wherein:
the compressor section includes a low pressure compressor; and
the second bearing is forward of the low pressure compressor relative to the engine longitudinal axis.
6 . The engine as recited in claim 1 , wherein:
the turbine section includes a low pressure turbine that drives the turbine shaft, and the low pressure turbine includes three or more stages; and
the drive gear system defines a speed reduction ratio between 2:1 and 13:1.
7 . The engine as recited in claim 1 , wherein:
the first bearing includes a first race configured to rotate with the gear carrier; and
the second bearing includes a second race configured to rotate with the gear carrier.
8 . A gas turbine engine comprising:
a plurality of blades that deliver air into a compressor section;
a drive gear system including an epicyclic transmission, the epicyclic transmission including a gear carrier, a ring gear encircling a sun gear, and a plurality of intermediate gears positioned between and enmeshing with the sun gear and the ring gear, wherein the plurality of intermediate gears are carried by the gear carrier;
a drive shaft interconnecting the year carrier and the plurality of blades; and
a turbine section that drives an input of the drive pear system through a turbine shaft;
wherein the drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system relative to an engine longitudinal axis;
wherein the ring gear is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing relative to the engine longitudinal axis;
wherein a third bearing is situated between an aft portion of the drive shaft and the turbine shaft.
9 . The engine as recited in claim 8 , wherein:
the second bearing is forward and radially outward of the third bearing relative to the engine longitudinal axis.
10 . A gas turbine engine comprising:
a plurality of blades that deliver air into a compressor section, the compressor section including a first compressor and a second compressor;
a drive gear system including a sun gear encircled by a ring gear, a plurality of intermediate gears positioned between and enmeshing with the sun gear and the ring gear, with the plurality of intermediate gears carried by a gear carrier;
a compliant flexure that couples the drive gear system to an engine case;
a drive shaft coupling the drive gear system to the plurality of blades;
a first spool extending along an engine longitudinal axis, the first spool including a first turbine driving an input of the drive gear system through a first shaft, and the first shaft including a flexible forward portion;
a second spool including a second turbine driving the second compressor through a second shaft;
a first bearing and a second bearing configured to rotate with the gear carrier, wherein the first and second bearings are located on opposite axial sides of the drive gear system relative to the engine longitudinal axis;
a third bearing engaging the first 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 engine longitudinal axis, and the first turbine has three or more stages.
11 . The engine as recited in claim 10 , wherein:
the third bearing is situated between an aft portion of the drive shaft and the first shaft.
12 . The engine as recited in claim 10 , wherein:
the first shaft includes a main portion and a flexible forward portion; and
the flexible forward portion interconnects the main portion of the first shaft and the input of the drive gear system.
13 . The engine as recited in claim 10 , wherein:
the second compressor is aft of the first compressor relative to the engine longitudinal axis; and
the second bearing is situated between the ring gear and the first compressor relative to the engine longitudinal axis.
14 . The engine as recited in claim 10 , wherein:
one of the first and second bearings is a thrust bearing, and another one of the first and second bearings is a non-thrust bearing.
15 . The engine as recited in claim 10 , wherein:
one of the second and third bearings is a thrust bearing, and another one of the second and third bearings is a non-thrust bearing.
16 . The engine as recited in claim 10 , wherein:
the second bearing supports an aft portion of the drive shaft relative to a rear support of a static structure; and
the rear support extends radially inward from a forward frame of the static structure at a position that is aft of the drive gear system relative to the engine longitudinal axis.
17 . The engine as recited in claim 16 , wherein:
the first bearing supports a forward portion of the drive shaft relative to a forward support that extends inwardly from the forward frame relative to the engine longitudinal axis.
18 . The engine as recited in claim 16 , wherein:
the third bearing is situated between the aft portion of the drive shaft and the first shaft.
19 . The engine as recited in claim 10 , wherein:
the first bearing includes a first race configured to rotate with the gear carrier; and
the second bearing includes a second race configured to rotate with the gear carrier.
Continuity (6)
Provisional Application
61789193
· Mar 15, 2013
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