公开(公告)号：US11421592B2

公开(公告)日：2022-08-23

申请号：US16416766

申请日：2019-05-20

Applicant: ROLLS-ROYCE plc

Inventor： Christopher T J Sheaf ,  Richard G Stretton ,  Chia Hui Lim

IPC: F02C7/00 ,  F02C7/04 ,  B64D27/26 ,  B64D29/02

Abstract: A gas turbine engine (100) for an aircraft comprises a pylon attachment (112) and a shaft (108) defining an engine centreline (110). The engine centreline lies in an engine central plane (120) which intersects the pylon attachment. The gas turbine engine comprises an intake (104) having a non-axisymmetric geometry and a medial plane (130) defining left and right halves of the intake. The left and right halves are configured for at least one of optimum cross wind performance, optimum incidence performance and optimum cruise performance when the medial plane is aligned with a vertical plane. The intake is installed so that the medial plane is angularly offset with respect to the engine central plane. The engine may be installed on a wing of an aircraft with the medial plane closer to its optimal orientation than is the case for a conventional engine.