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.

公开(公告)号：US11313241B2

公开(公告)日：2022-04-26

申请号：US17084821

申请日：2020-10-30

Applicant: ROLLS-ROYCE plc

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

IPC: F01D25/24 ,  F01D9/04 ,  F02C7/04

Abstract: A nacelle for a gas turbine engine having a longitudinal centre line includes an intake lip disposed at an upstream end of the nacelle. The intake lip includes a crown and a keel. The crown includes a crown leading edge and the keel includes a keel leading edge. The crown leading edge and the keel leading edge define a scarf line therebetween. The scarf line forms a scarf angle (θscarf) relative to a reference line perpendicular to the longitudinal centre line. A fan casing is disposed downstream of the intake lip and includes a casing leading edge. The casing leading edge defines a droop line normal to the casing leading edge. The droop line forms a droop angle (θdroop) relative to the longitudinal centre line. A relationship between the droop angle (θdroop) and the scarf angle (θscarf) is given by: θdroop=θscarf/1.5±1 degree.