The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Jan. 16, 2024

Filed:

Feb. 27, 2023
Applicant:

Rolls-royce Plc, London, GB;

Inventors:

Ian J. Bousfield, Nottingham, GB;

Duncan A. Macdougall, Derby, GB;

Assignee:

ROLLS-ROYCE plc, London, GB;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F02C 7/05 (2006.01); F02C 7/36 (2006.01);
U.S. Cl.
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);
Abstract

A gas turbine engine comprises 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 and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.


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