Front section stiffness ratio

A gas turbine engine comprising:

• a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of said fan rotor relative to a speed of said fan drive turbine;
• a fan case surrounding said fan rotor, and an inner core housing surrounding a compressor section, including a low pressure compressor;
• said fan rotor delivering air into a bypass duct defined between said fan case and a splitter wall of said inner core housing, and a rigid connection between said fan case and said inner core housing including a plurality of A-frames each including a pair of legs rigidly connected at a connection point to said fan case, and each leg in said pair extending away from said connection point in opposed circumferential directions to be connected to a compressor wall of said inner core housing to form an A-shape;
• the rigid connection also including a plurality of fan exit guide vanes rigidly connected to said fan case;
• and
• wherein a moment stiffness is defined about an axis extending perpendicular to a rotational axis of the gas turbine engine, and a moment stiffness ratio of a moment stiffness of the plurality of fan exit guide vanes to a moment stiffness of the combination of the plurality of A-frames, the compressor wall, and a fan intermediate case forward of the lower pressure compressor being greater than or equal to 0.50 and less than or equal to 2.0.