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.
Patent No.:
Date of Patent:
Jun. 11, 2024
Filed:
Aug. 22, 2022
Applicant:
Rolls-royce Plc, London, GB;
Inventors:
Nicholas Howarth, Derby, GB;
Gareth M Armstrong, Nottingham, GB;
Assignee:
ROLLS-ROYCE plc, London, GB;
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F01D 5/28 (2006.01); F02C 3/02 (2006.01); F02C 3/04 (2006.01); F02C 3/107 (2006.01); F02C 7/04 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01); F02K 3/068 (2006.01); F04D 19/02 (2006.01); F04D 29/68 (2006.01);
U.S. Cl.
CPC ...
F01D 5/145 (2013.01); F01D 5/141 (2013.01); F01D 5/28 (2013.01); F02C 3/02 (2013.01); F02C 3/04 (2013.01); F02C 3/107 (2013.01); F02C 7/04 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F02K 3/068 (2013.01); F04D 19/024 (2013.01); F04D 29/681 (2013.01);
Abstract
A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.