Forward load reduction structures for aft-most stages of high pressure compressors

A turbofan engine, comprising:

• a fan section;
• and
• a core turbine engine disposed downstream of the fan section, the core turbine engine comprising a compressor,
• wherein the compressor comprises:
• an outer circumferential support structure;
• an inner circumferential support structure positioned radially inward from the outer circumferential support structure, the inner circumferential support structure comprising an aft-most spacer arm and a forward spacer arm, the outer and inner circumferential support structures arranged concentrically around a longitudinal centerline;
• an aft-most stage comprising:
• an aft-most vane extending radially inward from the outer circumferential support structure, the aft-most vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
• an aft-most rotor extending radially from the aft-most spacer arm adjacent to the aft-most vane, where an intersection of the aft-most rotor and the aft-most spacer arm defines a centrally located first point;
• and
• a forward stage positioned forward of the aft-most stage, the forward stage comprising:
• a forward vane extending radially inward from the outer circumferential support structure, the forward vane comprising a root positioned at the outer circumferential support structure and a tip positioned radially inward from the root, and
• a forward rotor extending radially from the forward spacer arm adjacent to the forward vane, where an intersection of the forward rotor and the forward spacer arm defines a centrally located second point,
• wherein an arrangement of a first line extending through the first point and the second point forms an angle with a second line extending parallel to the longitudinal centerline and extending through the tip of the aft-most vane and the tip of the forward vane, the angle being greater than 0° and less than or equal to 45°.