US 12,110,804 B2
Super-cooled ice impact 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 Nov. 30, 2023, as Appl. No. 18/524,490.
Application 18/524,490 is a continuation of application No. 18/114,583, filed on Feb. 27, 2023, granted, now 11,873,731.
Application 18/114,583 is a continuation of application No. 17/218,617, filed on Mar. 31, 2021, granted, now 11,619,135.
Application 17/218,617 is a continuation of application No. 16/813,830, filed on Mar. 10, 2020, granted, now 10,995,677, issued on May 4, 2021.
Application 16/813,830 is a continuation of application No. 16/686,274, filed on Nov. 18, 2019, granted, now 10,612,471, issued on Apr. 7, 2020.
Claims priority of application No. 1820423 (GB), filed on Dec. 14, 2018.
Prior Publication US 2024/0093610 A1, Mar. 21, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/14 (2006.01); F02C 7/05 (2006.01); F02C 7/36 (2006.01)
CPC F01D 5/141 (2013.01) [F01D 5/142 (2013.01); F02C 7/05 (2013.01); F02C 7/36 (2013.01); F05D 2220/32 (2013.01); F05D 2240/24 (2013.01); F05D 2240/303 (2013.01); F05D 2260/94 (2013.01)] 19 Claims
OG exemplary drawing
 
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, the reduction gearbox having a gear ratio of at least 3,
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 and second blades comprising respective leading edges, trailing edges and tips,
wherein a ratio of a tip maximum thickness of the first blades to a tip maximum thickness of the second blades is less than 5; and
wherein the ratio of the tip maximum thickness of the first blades to the tip maximum thickness of the second blades is greater than 2.5.