公开(公告)号：US20200063604A1

公开(公告)日：2020-02-27

申请号：US16544996

申请日：2019-08-20

Applicant: ROLLS-ROYCE plc

Inventor： Richard G STRETTON ,  David WESTON ,  Nicholas P ROSE

IPC: F01D25/24

Abstract: There is disclosed a gas turbine engine for an aircraft comprising: a propulsive fan having a plurality of fan blades; a fan casing; and an air intake; wherein the air intake is mechanically coupled to the fan casing at a point having an axial position that is within a range of axial positions from a first axial position that is rearward of the leading edge of the fan blade at its radial tip by an axial component of a blade chord length, to a second axial position that is forward of the leading edge of the fan blade tip by an axial component of the blade chord length.