US 12,359,628 B2
High power epicyclic gearbox and operation thereof
Mark Spruce, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Sep. 10, 2024, as Appl. No. 18/829,971.
Application 18/829,971 is a continuation of application No. 18/131,493, filed on Apr. 6, 2023, granted, now 12,116,938.
Application 18/131,493 is a continuation of application No. 17/576,218, filed on Jan. 14, 2022, granted, now 11,725,591, issued on Aug. 15, 2023.
Application 17/576,218 is a continuation of application No. 17/066,713, filed on Oct. 9, 2020, granted, now 11,268,452, issued on Mar. 8, 2022.
Application 17/066,713 is a continuation of application No. 16/821,227, filed on Mar. 17, 2020, granted, now 10,851,715, issued on Dec. 1, 2020.
Claims priority of application No. 1917773 (GB), filed on May 12, 2019.
Prior Publication US 2024/0426252 A1, Dec. 26, 2024
Int. Cl. F02K 3/06 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F02K 3/06 (2013.01); F05D 2200/14 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
a gearbox that is configured to:
receive an input from the core shaft, and
output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; wherein
a product of: (a radial bending stiffness of the fan shaft at the input to the fan)×(a radial bending stiffness of the fan shaft at the output of the gearbox)
is greater than or equal to 1.2×1013 (N/m)2.