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:
May. 18, 2021

Filed:

Jan. 31, 2020
Applicant:

Rolls-royce Plc, London, GB;

Inventors:

Chathura K Kannangara, Derby, GB;

Jillian C Gaskell, Derby, GB;

Stewart T Thornton, Derby, GB;

Timothy Philp, Derby, GB;

Assignee:

ROLLS-ROYCE pic, London, GB;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F01D 25/28 (2006.01); F02C 7/36 (2006.01); F01D 25/24 (2006.01); F16H 1/28 (2006.01); F02K 3/06 (2006.01); F02C 7/20 (2006.01);
U.S. Cl.
CPC ...
F01D 5/14 (2013.01); F01D 25/243 (2013.01); F01D 25/28 (2013.01); F02C 7/20 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F16H 1/28 (2013.01); F05D 2220/32 (2013.01); F05D 2240/14 (2013.01); F05D 2240/24 (2013.01); F05D 2240/90 (2013.01); F05D 2260/31 (2013.01); F05D 2260/40311 (2013.01);
Abstract

A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing. The engine includes a front mount arranged for connection to a pylon; and a fan located upstream of the engine core. The outer core casing includes a first flange connection that: is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A front mount position ratio of: is equal to or less than 1.18.


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