Patent ID: 11927106
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 12:
13. 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 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 core engine 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 said core engine to form an A-shape; and
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 non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise, said acoustic feature including said non-structural fan exit guide vanes being formed with chambers and a covering perforated face sheet.