Systems and methods involving multiple torque paths for gas turbine engines

A turbine engine, comprising:

• a compressor;
• a gear assembly;
• a turbine;
• a shaft coupled to the turbine;
• a thrust bearing supporting the shaft, and comprising a tapered roller bearing;
• a first spool segment coupling the compressor to the shaft;
• and
• a second spool segment coupling the gear assembly to the shaft;
• wherein the first and the second spool segments are each mechanically connected to the shaft at an intersection, and the thrust bearing is located aft of the first spool segment at the intersection between the shaft and the spool segments.

A turbine engine, comprising:

• a compressor;
• a fan;
• a turbine;
• a shaft coupled to the turbine;
• a thrust bearing supporting the shaft, and comprising a tapered roller bearing;
• a first spool segment coupling the compressor to the shaft;
• and
• a second spool segment coupling the fan to the shaft;
• wherein the first and the second spool segments are each mechanically connected to the shaft at an intersection, and the thrust bearing is located aft of the first spool segment at the intersection between the shaft and the spool segments.