US 11,732,603 B2
Ice crystal protection for a gas turbine engine
Ian J Bousfield, Nottingham (GB); and Duncan A MacDougall, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Oct. 20, 2022, as Appl. No. 17/969,826.
Application 17/969,826 is a continuation of application No. 17/235,234, filed on Apr. 20, 2021, granted, now 11,512,607.
Application 17/235,234 is a continuation of application No. 16/437,501, filed on Jun. 11, 2019, granted, now 11,002,149, issued on May 11, 2021.
Claims priority of application No. 1902549 (GB), filed on Feb. 26, 2019.
Prior Publication US 2023/0045400 A1, Feb. 9, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 25/02 (2006.01); F01D 5/14 (2006.01); F04D 29/32 (2006.01)
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
OG exemplary drawing
 
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.