公开(公告)号：US11578617B2

公开(公告)日：2023-02-14

申请号：US17320297

申请日：2021-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Fernando L Tejero Embuena ,  David G Macmanus ,  Christopher Tj Sheaf

IPC: F01D25/24 ,  B64D27/12 ,  B64D29/02

Abstract: A nacelle for a gas turbine engine includes a leading edge at an upstream side of the nacelle. The nacelle further includes a trailing edge at a downstream side of the nacelle. The nacelle further includes an outer surface disposed between the leading edge and the trailing edge. The nacelle further includes a concave section continuous with the outer surface and disposed proximal to the trailing edge. The concave section includes an upstream end and a downstream end spaced apart from the upstream end. The concave section is curved radially inwards relative to the outer surface between the upstream end and the downstream end.

公开(公告)号：US11408306B2

公开(公告)日：2022-08-09

申请号：US17152075

申请日：2021-01-19

Applicant: ROLLS-ROYCE plc

Inventor： Fernando L Tejero Embuena ,  David G. Macmanus ,  Christopher T J Sheaf

IPC: F01D25/24 ,  B64D27/12 ,  F02C7/04

Abstract: A nacelle for housing a fan within a gas turbine engine having a longitudinal centre line includes a leading edge and a trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. An azimuthal angle (θ) is defined about the longitudinal centre line. The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.