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:
Jan. 24, 2023
Filed:
Sep. 03, 2021
Applicant:
Rolls-royce Plc, London, GB;
Inventors:
Craig W Bemment, Derby, GB;
Pascal Dunning, Derby, GB;
Assignee:
ROLLS-ROYCE plc, London, GB;
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 9/28 (2006.01); F01D 11/14 (2006.01); F01D 13/00 (2006.01); F01D 25/24 (2006.01);
U.S. Cl.
CPC ...
F02C 9/28 (2013.01); F01D 11/14 (2013.01); F01D 13/003 (2013.01); F01D 25/24 (2013.01); F05D 2200/14 (2013.01); F05D 2270/313 (2013.01);
Abstract
A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.