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

Claim 0:
1. 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 said leg extending away from said connection point and connected to a compressor wall of said inner core housing; and
a plurality of fan exit guide vanes rigidly connected to said fan case; and
a lateral stiffness is defined in a radial direction, a lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of rigid mounts, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.