Geared turbofan engine with inter-shaft deflection feature
A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a first turbine driving the first compressor and a second turbine driving the second compressor. An inner shaft defines a driving link between the second compressor and the second turbine and an outer shaft defines a driving link between the first compressor and the first turbine. The inner shaft and the outer shaft are concentric about a common axis of rotation. A bumper is disposed on the inner shaft within an axial region common to an aft portion of the outer shaft for accommodating interaction between the inner and outer shafts during high load conditions.
1. A turbine engine comprising:
a compressor section including a first compressor section and a second compressor section;
a turbine section including a first turbine section driving the first compressor section through an inner shaft and a second turbine section driving the second compressor section through an outer shaft, wherein the outer shaft includes an aft end;
a bearing assembly supporting rotation of the outer shaft, the bearing assembly spaced axially forward of the aft end;
a bumper located between the inner shaft and the outer shaft for accommodating interaction between the inner shaft and the outer shaft, wherein the aft end of the outer shaft is disposed annularly about the bumper; and
a fastening member attached to the aft end of the outer shaft for securing a portion of the bearing assembly to the outer shaft, wherein the fastening member is spaced axially aft of the bearing assembly within an axial length disposed at least partially about the bumper.
2. The turbine engine as recited in claim 1 , wherein the bumper comprises a portion of one of the inner and outer shafts.
3. The turbine engine as recited in claim 1 , wherein the bumper comprises a portion of the inner shaft.
4. The turbine engine as recited in claim 3 , wherein the bumper comprises a bumper diameter greater than diameters of the inner shaft surrounding the bumper diameter.
5. The turbine engine as recited in claim 4 , wherein a ratio of the diameters of the inner shaft surrounding the bumper diameter is 1.032.
6. The turbine engine as recited in claim 1 , wherein the inner shaft includes a flange extending radially outward and spaced apart axially aft of the bumper.
7. The turbine engine as recited in claim 1 , including a plurality of fan blades rotatable about an axis and driven by the turbine section through a geared architecture.
8. A gas turbine engine comprising:
a compressor section including a first compressor and a second compressor;
a turbine section including a first turbine driving the first compressor and a second turbine driving the second compressor;
an inner shaft defining a driving link between the second compressor and the second turbine;
an outer shaft defining a driving link between the first compressor and the first turbine, wherein the inner shaft and the outer shaft are concentric about a common axis of rotation;
a bearing assembly supporting rotation of the outer shaft, the bearing assembly spaced axially forward of an aft end portion of the outer shaft;
a bumper disposed on the inner shaft within an axial region common to the aft end portion of the outer shaft for accommodating interaction between the inner and outer shafts; and
a fastener attached to the aft end portion within the axial region of the aft end portion of the outer shaft, the fastener threaded to a threaded outer diameter of the outer shaft at the aft end portion.
9. The gas turbine engine as recited in claim 8 , wherein the inner shaft includes a first diameter within the axial region on either side of the bumper and the bumper comprises a bumper diameter larger than the first diameter.
10. The gas turbine engine as recited in claim 8 , wherein the inner shaft includes a radially extending flange that is disposed aft of the bumper and the axial region.
11. The gas turbine engine as recited in claim 8 , wherein the bumper is continuous about a circumference of the inner shaft within the axial region.