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:
Mar. 24, 2020
Filed:
Jun. 25, 2019
Rolls-royce Plc, London, GB;
Chathura K Kannangara, Derby, GB;
Jillian C Gaskell, Derby, GB;
Stewart T Thornton, Derby, GB;
Timothy Philp, Derby, GB;
ROLLS-ROYCE plc, London, GB;
Abstract
A gas turbine engine () for an aircraft comprises an engine core () comprising: a compressor system comprising a first, lower pressure, compressor (), and a second, higher pressure, compressor (); and an outer core casing () surrounding the compressor system. The gas turbine engine further comprises a fan () located upstream of the engine core (), the fan comprising a plurality of fan blades. The outer core casing comprises: a first flange connection () arranged to allow separation of the outer core casing () at an axial position of the first flange connection (), the first flange connection () having a first flange radius (), wherein the first flange connection () is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor () and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor (). A fan blade mass ratio of: is equal to or less than 19.0 mm/lb.