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 rotor blade with a blade trailing edge, wherein an intermediate case is arranged between the compressor case and a high pressure compressor case;
• and
• wherein the support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge, and the support structure trailing edge arranged axially forward of the blade trailing edge, wherein a forward attachment extends from the support structure to the inlet case, wherein the intermediate case supports a rear portion of the compressor case near a compressed air bleed valve, and comprising a rearward attachment extending from the support structure to the intermediate case, wherein the front and rearward attachments are generally equidistant from the support structure to their respective forward and rearward attachment.