Patent ID: 11879397
Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
Field: Mechanical elements (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
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 comprising a plurality of fan blades; and
a gearbox that receives an input from the core shaft and outputs drive to the fan to drive the fan about a rotational axis at a lower rotational speed than the core shaft, wherein the gearbox is an epicyclic gearbox with a plurality of planet gears arranged in at least first and second sets of planet gears, the planet gears of the first set being positioned displaced relative to the planet gears of the second set in a direction 1) parallel to the rotational axis and also 2) circumferentially around the rotational axis.