Gas turbine engine front architecture

A turbine engine comprising:

• a fan case surrounding a fan rotatable about an axis;
• a core supported relative to the fan case by a support structure and arranged downstream from the fan, the core including a core housing having an inlet case arranged to receive airflow from the fan, a compressor case axially adjacent to the inlet case and surrounding a compressor stage having a first rotor blade with a blade leading edge and a second rotor blade with a blade trailing edge, both blades rotatable about the axis, and an intermediate case arranged axially adjacent to the compressor case, the support structure arranged axially forward of the intermediate case;
• a gear train interconnected between the fan and a spool that is arranged within the core;
• and
• wherein the support structure is axially aligned with the compressor case, the support structure including a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge, the support leading edge arranged axially rearward of the blade leading edge, and the support structure trailing edge arranged axially forward of the blade trailing edge, wherein forward and rearward attachments extend from the support structure respectively to the inlet case and the intermediate case.