초록

A gas turbine engine includes a shaft supported by first and second bearings for rotation relative to an inlet case. The first and second bearings are positioned within a common bearing compartment.

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1. A gas turbine engine comprising: a shaft defining an axis of rotation;an inlet case comprising a non-rotating core housing that defines a core flowpath through the gas turbine engine, and wherein the inlet case comprises a first inlet case portion defining an inlet case flow path and a second inl

1. A gas turbine engine comprising: a shaft defining an axis of rotation;an inlet case comprising a non-rotating core housing that defines a core flowpath through the gas turbine engine, and wherein the inlet case comprises a first inlet case portion defining an inlet case flow path and a second inlet case portion removably secured to the first inlet case portion;a first bearing supporting the shaft for rotation relative to the inlet case, the first bearing being positioned within a bearing compartment formed between the shaft and the second inlet case portion;a second bearing also supporting the shaft for relative rotation to the inlet case, the second bearing also being positioned within the bearing compartment, and wherein the first and second bearings are mounted to the second inlet case portion; anda compressor section with at least a low pressure compressor and a high pressure compressor, and which includes a plurality of vanes and a rotor supporting a plurality of blades interspersed with the plurality of vanes, and wherein the first and second bearings are positioned radially between the shaft and the blades, and wherein the second inlet case portion includes a fore end that is removably secured to the first inlet case portion at a first connection interface that is positioned forward of the rotor and the compressor section. 2. The gas turbine engine according to claim 1, wherein the compressor section includes a compressor case having a first compressor case portion defining a compressor case flow path and a second compressor case portion removably secured to the first compressor case portion at a second connection interface that is positioned aft of the first connection interface, and wherein the second inlet case portion extends aft of the first inlet case portion such that an aft end of the second inlet case portion is surrounded by the compressor section. 3. The gas turbine engine according to claim 2, wherein the shaft comprises a main shaft and a hub secured to the main shaft, and wherein the rotor is mounted to the hub, the hub supporting the first and the second bearings, and wherein the second inlet case portion extends forward of the rotor and the compressor section. 4. The gas turbine engine according to claim 3, including a geared architecture coupled to the hub, and a fan coupled to and rotationally driven by the geared architecture. 5. The gas turbine engine according to claim 2, wherein the low pressure compressor includes the rotor which is mounted for rotation with the shaft, and wherein the fore end of the second inlet case portion extends forward of the rotor. 6. The gas turbine engine according to claim 2, wherein the first and second bearings are positioned aft of the first connection interface and forward of the second connection interface. 7. The gas turbine engine according to claim 1, wherein the first bearing is a ball bearing and the second bearing is a roller bearing, and wherein the first and second bearings are positioned downstream of a geared architecture that couples the shaft to a fan. 8. The gas turbine engine according to claim 7, wherein the ball bearing is located aft of the roller bearing, and wherein the ball and roller bearings are generally concentric and axially spaced apart from each other. 9. The gas turbine engine according to claim 1, wherein the first and second bearings are positioned axially aft of the first connection interface. 10. The gas turbine engine according to claim 1, wherein the second inlet case portion includes a fore flange portion that directly supports the second bearing and an aft flange portion that directly supports the first bearing. 11. The gas turbine engine according to claim 10, wherein the fore flange portion is radially closer to the axis of rotation than the aft flange portion. 12. The gas turbine engine according to claim 11, including a hub having an aft hub end coupled to the shaft and fore hub end coupled to a flex shaft at a second connection interface, wherein the flex shaft drives a geared architecture, and wherein the fore hub end directly supports the second bearing and the aft hub end directly supports the first bearing, and wherein the second connection interface is positioned axially between the first and second bearings. 13. The gas turbine engine according to claim 12, wherein the fore hub end is spaced further radially away from the axis of rotation than the aft hub end, and wherein the first and second bearings are generally concentric and axially spaced apart from each other. 14. The gas turbine engine according to claim 1, including a geared architecture coupled to the shaft and a fan coupled to and rotationally driven by the geared architecture, and wherein the geared architecture includes an inner gear driven by the shaft, a plurality of outer gears meshing with the inner gear, and a ring gear in meshing engagement with the outer gears, the ring gear driving the fan. 15. The gas turbine engine according to claim 1, wherein the compressor section includes a compressor case that is attached to the inlet case, and including at least one strut positioned upstream of the compressor section and held fixed to the non-rotating core housing to support the inlet case. 16. The gas turbine engine according to claim 15, and wherein the first bearing comprises a fore bearing and the second bearing comprises an aft bearing that is spaced axially aft of the fore bearing, and wherein the fore bearing is in a radially overlapping relationship with the at least one strut. 17. A gas turbine engine comprising: a shaft defining an axis of rotation, wherein the shaft comprises a main shaft and a hub secured to the main shaft;a first bearing supporting the shaft for rotation relative to an inlet case, the first bearing being positioned within a bearing compartment formed between the shaft and the inlet case;a second bearing also supporting the shaft for relative rotation to the inlet case, the second bearing also being positioned within the bearing compartment;a compressor section with a compressor case having a first compressor case portion defining a compressor case flow path and a second compressor case portion removably secured to the first compressor case portion;wherein the inlet case comprises a first inlet case portion defining an inlet case flow path and a second inlet case portion removably secured to the first inlet case portion, the first and second bearings being mounted to the second inlet case portion, and wherein a portion of the second inlet case portion is surrounded by a portion of the compressor section, and wherein the compressor section includes a rotor mounted to the hub, the hub supporting the first and the second bearings;a geared architecture coupled to the hub, and a fan coupled to and rotationally driven by the geared architecture; anda flex shaft having at least one bellow, and wherein the flex shaft is secured to the hub at an aft end and is coupled to the geared architecture at a fore end, and wherein the aft end of the flex shaft is coupled to the hub at a connection interface, and wherein the connection interface is positioned aft of the second bearing. 18. The gas turbine engine according to claim 17, wherein the geared architecture includes a sun gear supported on the fore end of the flex shaft, a torque frame supporting multiple circumferentially arranged star gears intermeshing with the sun gear, and a ring gear meshing with the star gears. 19. The gas turbine engine according to claim 17, wherein the hub includes a fore hub end and an aft hub end, the second bearing being directly supported by the fore hub end and the first bearing being supported by the aft hub end with the connection interface being positioned between the fore and aft hub ends. 20. The gas turbine engine according claim 17, wherein the first bearing is a ball bearing and the second bearing is a roller bearing. 21. A gas turbine engine comprising: a core housing providing a core flow path, the core housing comprising a non-rotating inlet case having at least a first inlet case portion defining an inlet case flow path and a second inlet case portion removably secured to the first inlet case portion;a shaft supporting a compressor section arranged within the core flow path;a geared architecture coupled to the shaft and a fan coupled to and rotationally driven by the geared architecture;first and second bearings mounted to the second inlet case portion and supporting the shaft for rotation relative to the core housing, and wherein the first and second bearings are positioned within a common bearing compartment positioned within the compressor section; anda compressor section with at least a low pressure compressor and a high pressure compressor, and which includes a plurality of vanes and a rotor supporting a plurality of blades interspersed with the plurality of vanes, and wherein the first and second bearings are positioned radially between the shaft and the blades, and wherein the second inlet case portion includes an aft end that is surrounded by the compressor section and a fore end that extends forward of the rotor and the compressor section. 22. The gas turbine engine according to claim 21, wherein the shaft includes a main shaft, a hub secured to the main shaft, and a flex shaft having at least one bellow, and wherein the flex shaft is secured to the hub at an aft end and is coupled to the geared architecture at a fore end, and wherein the first and second bearings are directly supported by the hub. 23. The gas turbine engine according to claim 21, wherein the first bearing is a ball bearing and the second bearing is a roller bearing. 24. The gas turbine engine according to claim 23, wherein the ball bearing is located aft of the roller bearing. 25. The gas turbine engine according to claim 21, wherein the bearing compartment is formed between the shaft and the second inlet case portion, and wherein the first and second bearings are positioned axially aft of a first connection interface between the first and second inlet case portions. 26. The gas turbine engine according to claim 25, wherein the second inlet case portion includes a fore flange portion that directly supports the second bearing and an aft flange portion that directly supports the first bearing. 27. The gas turbine engine according to claim 26, including a hub having an aft hub end coupled to the shaft and fore hub end coupled to a flex shaft at a second connection interface, wherein the flex shaft drives a geared architecture, and wherein the fore hub end directly supports the second bearing and the aft hub end directly supports the first bearing, and wherein the second connection interface is positioned axially between the first and second bearings. 28. The gas turbine engine according to claim 27, wherein the fore flange portion is radially closer to the axis of rotation than the aft flange portion, and wherein the fore hub end is spaced further radially away from the axis of rotation than the aft hub end, and wherein the first and second bearings are generally concentric and axially spaced apart from each other. 29. The gas turbine engine according to claim 21, wherein the first and second bearings are positioned downstream of the geared architecture. 30. The gas turbine engine according to claim 21, wherein the first and second inlet case portions are connected to each other at a first connection interface, and including at least one strut positioned upstream of the compressor section and held fixed to the core housing to support the inlet case, and wherein the first connection interface is radially inward of the strut such that the first connection interface and strut overlap each other in a radial direction. 31. The gas turbine engine according to claim 30, and wherein the first bearing comprises a fore bearing and the second bearing comprises an aft bearing that is spaced axially aft of the fore bearing, and wherein the fore bearing is in a radially overlapping relationship with the at least one strut. 32. The gas turbine engine according to claim 21, wherein the first inlet case portion is removably secured to the second inlet case portion at a first connection interface, and wherein the compressor section has a compressor case having at least a first compressor case portion defining a compressor case flow path and a second compressor case portion removably secured to the first compressor case portion at a second connection interface that is positioned aft of the first connection interface, and wherein the second inlet case portion extends aft of the first inlet case portion such that the aft end of the second inlet case portion is surrounded by the compressor section. 33. The gas turbine engine according to claim 32, wherein the low pressure compressor includes the rotor which mounted for rotation with the shaft, and wherein the fore end of the second inlet case portion extends forward of the rotor. 34. The gas turbine engine according to claim 32, wherein the first and second bearings are positioned aft of the first connection interface and forward of the second connection interface.