CPC F01D 25/02 (2013.01) [F01D 5/141 (2013.01); F01D 5/147 (2013.01); F04D 29/324 (2013.01); F05D 2220/32 (2013.01); F05D 2240/303 (2013.01); F05D 2240/307 (2013.01)] | 20 Claims |
1. A gas turbine engine comprising:
a fan mounted to rotate about a main longitudinal axis; and
an engine core comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; wherein
the compressor comprises a plurality of stages, each stage comprising a respective rotor and stator, a first stage of said plurality of stages being arranged at an inlet and comprising a first rotor with a plurality of first rotor blades,
each of the plurality of first rotor blades extends chordwise from a leading edge to a trailing edge,
a ratio of a maximum leading edge radius of each of the plurality of first rotor blades to a fan diameter is comprised between 1.4×10−4 and 3.6×10−4, the maximum leading edge radius of each of the plurality of first rotor blades being the maximum radius that is defined by the leading edge in circumferential cross-section, and
the fan diameter is greater than 220 cm, or greater than 230 cm, or greater than 240 cm.
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