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:
Jun. 27, 2023

Filed:

May. 28, 2021
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:
Assistant Examiner:
Int. Cl.
CPC ...
F02C 7/05 (2006.01); F02C 7/30 (2006.01); F01D 25/02 (2006.01); F02K 1/82 (2006.01); F01D 21/10 (2006.01); F02C 7/04 (2006.01); F01D 5/14 (2006.01);
U.S. Cl.
CPC ...
F02C 7/05 (2013.01); F01D 5/143 (2013.01); F01D 21/10 (2013.01); F01D 25/02 (2013.01); F02C 7/04 (2013.01); F02C 7/30 (2013.01); F02K 1/82 (2013.01);
Abstract

A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.


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