US 12,421,903 B2
Geared gas turbine engine
Nicholas Howarth, Derby (GB); and Gareth M Armstrong, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Jul. 26, 2024, as Appl. No. 18/785,906.
Application 18/785,906 is a continuation of application No. 18/236,666, filed on Aug. 22, 2023, granted, now 12,071,901.
Application 18/236,666 is a continuation of application No. 17/987,516, filed on Nov. 15, 2022, granted, now 11,781,491, issued on Oct. 10, 2023.
Application 17/987,516 is a continuation of application No. 17/731,877, filed on Apr. 28, 2022, granted, now 11,698,030, issued on Jul. 11, 2023.
Application 17/731,877 is a continuation of application No. 17/171,439, filed on Feb. 9, 2021, granted, now 11,346,287, issued on May 31, 2022.
Application 17/171,439 is a continuation of application No. 16/443,938, filed on Jun. 18, 2019, granted, now 10,961,916, issued on Mar. 30, 2021.
Claims priority of application No. 1903261 (GB), filed on Mar. 11, 2019.
Prior Publication US 2025/0012221 A1, Jan. 9, 2025
Int. Cl. F02C 7/36 (2006.01); F01D 15/12 (2006.01); F02C 3/113 (2006.01)
CPC F02C 7/36 (2013.01) [F01D 15/12 (2013.01); F02C 3/113 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a combustor;
a fan comprising a plurality of fan blades; and
a gearbox that receives an input from a core shaft that is connected to at least a part of the turbine, the gearbox outputting drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, wherein
the blade height of a most downstream compressor blade, defined as the radius of a leading edge at a tip of the blade minus the radius of a point where the leading edge intersects a radially inner gas-washed surface, is in a range from 1.5 cm to 2.0 cm, and
the radius at a tip of a most downstream turbine blade is 40 cm to 60 cm.