Geared turbofan bearing arrangement
A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.
1. A geared turbofan gas turbine engine assembly comprising:
a core section including a compressor section, a combustor section and a turbine section;
a fan section including a gearbox and a fan;
a low pressure spool supporting a low pressure turbine within the turbine section and driving the fan through the gearbox; and
a high pressure spool supporting a high pressure compressor within the compressor section and a high pressure turbine within the turbine section, wherein the low pressure spool is supported for rotation about the axis at a forward position by a forward roller bearing and at an aft position by a thrust bearing, wherein the forward position of the forward roller bearing is aft of the gearbox and forward of the high pressure compressor.
2. The gas turbine engine assembly as recited in claim 1 , wherein the high pressure spool is supported for rotation by a thrust bearing at a forward position and a roller bearing at an aft position.
3. The gas turbine engine assembly as recited in claim 2 , wherein the roller bearing supporting rotation of the low pressure spool is forward of the thrust bearing supporting rotation of the high spool.
4. The gas turbine engine assembly as recited in claim 3 , wherein the aft thrust bearing supporting rotation of the low pressure spool is aft of the roller bearing supporting rotation of the high pressure spool.
5. The gas turbine engine assembly as recited in claim 1 , wherein the aft thrust bearing supporting rotation of the low pressure spool is supported by a turbine exhaust case.
6. The gas turbine engine assembly as recited in claim 1 , including an intermediate pressure spool supported between the low pressure spool and the high pressure spool, the intermediate pressure spool supporting an intermediate pressure compressor within the compressor section and an intermediate pressure turbine in the turbine section.
7. The gas turbine engine assembly as recited in claim 6 , wherein the intermediate pressure spool includes a forward thrust bearing and an aft roller bearing, wherein the forward thrust bearing is aft of the roller bearing supporting rotation of the low pressure spool.
8. The gas turbine engine assembly as recited in claim 1 , wherein the gearbox is driven by the low pressure spool.
9. The gas turbine engine assembly as recited in claim 8 , wherein the fan is supported by first and second roller bearings.
10. A geared turbofan gas turbine engine assembly comprising:
a core section including a compressor section, a combustor section and a turbine section;
a turbofan section including a gearbox and a fan;
a low pressure spool supporting a low pressure turbine within the turbine section and driving the fan through the gearbox;
an intermediate pressure spool supporting an intermediate pressure compressor within the compressor section and an intermediate pressure turbine within the turbine section; and
a high pressure spool supporting a high pressure compressor within the compressor section and a high pressure turbine within the turbine section, wherein the low pressure spool is supported for rotation about the axis at a forward position by a forward roller bearing and at an aft position by a thrust bearing, wherein the forward position of the forward roller bearing is aft of the gearbox.
11. The geared turbofan gas turbine engine assembly as recited in claim 10 , wherein the thrust bearing supporting the low pressure spool is supported by a turbine exhaust case.
12. The geared turbofan gas turbine engine assembly as recited in claim 10 , wherein the high pressure spool is supported by a roller bearing disposed axially within the combustor section.
13. The gas turbine engine assembly as recited in claim 12 , wherein the high pressure spool is supported for rotation by a thrust bearing at a forward position and the roller bearing disposed axially within the combustor section.
14. The gas turbine engine assembly as recited in claim 12 , wherein the roller bearing supporting rotation of the low pressure spool is forward of the thrust bearing supporting rotation of the high pressure spool.
15. The gas turbine engine assembly as recited in claim 10 , wherein the aft thrust bearing supporting rotation of the low pressure spool is aft of a roller bearing supporting rotation of the intermediate pressure spool.