LPC flowpath shape with gas turbine engine shaft bearing configuration

A gas turbine engine comprising:

• a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath, wherein the inlet case includes a first inlet case portion defining the inlet case flow path, and a bearing support portion is removably secured to the inlet case portion;
• a fan arranged fluidly upstream of the core housing;
• a shaft providing a rotational axis;
• a geared architecture coupled to the shaft, and the fan coupled to and rotationally driven by the geared architecture;
• a hub operatively supported by the shaft;
• a rotor connected to the hub and supporting a compressor section arranged fluidly downstream from the inlet case, the compressor section being arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path, the core flowpath having an inner diameter and an outer diameter, wherein the at least a portion of the inner diameter has an increasing slope angle relative to the rotational axis;
• a first bearing mounted to the hub and supporting the shaft relative to one of the intermediate case and the inlet case, the first bearing mounted to the bearing support portion;
• and
• a second bearing mounted to the hub and supporting the shaft relative to the other of the intermediate case and the inlet case.