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 flow path;
• a fan:
• a geared architecture;
• a first shaft supporting a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path, wherein the first shaft is configured to drive the fan through the geared architecture;
• a first bearing supporting the first shaft relative to the inlet case;
• a second bearing supporting a second shaft relative to the intermediate case;
• a third bearing supporting the first shaft relative to the inlet case;
• and
• a low pressure compressor hub mounted to the first shaft, the low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing, the low pressure compressor hub mounted to the low pressure compressor hub, the low pressure compressor hub supporting the first bearing, the first and third bearings secured onto and engaging the low pressure compressor hub.