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

Claim 13:
14. 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 maximum leading edge radius of the first blades is greater than 0.4 mm, and the maximum leading edge radius of the second blades is comprised between 0.1 and 0.3 mm, the maximum leading edge radius of the first blades being a maximum radius that is defined by the leading edge of the first blades in circumferential cross-section and the maximum leading edge radius of the second blades being a maximum radius that is defined by the leading edge of the second blades in circumferential cross-section.