Patent ID: 11927106
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 a core engine with a compressor section, including a low pressure compressor, said low pressure compressor having four to six stages;
said fan rotor delivering air into a bypass duct defined between said fan case and said core engine, and a rigid connection between said fan case and said core engine including a plurality of aft connecting members rigidly connected to said fan case, and to said core engine at a location downstream of said low pressure compressor;
a plurality of fan exit guide vanes rigidly connected to said fan case, with said plurality of fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to said core engine and non-structural fan exit guide vanes; and
said structural fan exit guide vanes include more than 0% and less than or equal to 55% of the plurality of fan exit guide vanes including the non-structural fan exit guide vane.