Patent ID: 11933190
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 16:
17. 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 rigid mounts each including at least one leg rigidly connected at a connection point to said fan case, and each leg extending away from said connection point and connected to a compressor wall of said inner core housing;
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 rigid mounts, 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.