| 摘要 |
A gas turbine engine assembly (10) is provided. The gas turbine engine assembly (10) includes a core gas turbine engine (13) including a high-pressure turbine (18). The gas turbine engine assembly (10) further includes a fan assembly (12) coupled to the core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine. The gas turbine engine assembly (10) further includes a low-pressure turbine (20) coupled to the core gas turbine engine, the low-pressure turbine coupled downstream from the core gas turbine engine, the low-pressure turbine includes a disk (105), a flange (107) formed with the disk, a plurality of splines (108) formed in the flange. The gas turbine engine assembly (10) further includes a shaft (31) including a first end (120) coupled to the fan assembly and a second end (122) that includes a plurality of splines. The gas turbine engine assembly (10) further includes a differential bearing (170) coupled between the shaft and the high-pressure turbine (18), the differential bearing configured to provide rotational support for the high--pressure turbine.
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