Patent ID: 11873731
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A gas turbine engine comprising:
a fan mounted to rotate about a main longitudinal axis,
an engine core comprising, in axial flow series, a compressor, a combustor, and a turbine coupled to the compressor through a shaft,
a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft,, wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first blades and second blades comprising respective leading edges, trailing edges and tips,, wherein a ratio of a maximum leading edge radius of the first blades to a minimum leading edge radius of the first blades is greater than 2.5, the maximum leading edge radius being a maximum radius that is defined by the leading edge of the first blades in circumferential cross-section and the minimum leading edge radius being a minimum radius that is defined by the leading edge of the first blades in circumferential cross-section.