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.

公开(公告)号：US11519330B2

公开(公告)日：2022-12-06

申请号：US17231130

申请日：2021-04-15

Applicant: ROLLS-ROYCE plc

Inventor： Robert E Christie ,  David G MacManus ,  Christopher T J Sheaf

IPC: F02C7/045 ,  B64D33/02 ,  F02K3/06

Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The nacelle further includes a protrusion extending radially inward from the air intake downstream of the intake lip. The protrusion extends circumferentially by a protrusion angle (θp) with respect to the longitudinal centre line of the gas turbine engine.

公开(公告)号：US11415048B2

公开(公告)日：2022-08-16

申请号：US17231421

申请日：2021-04-15

Applicant: ROLLS-ROYCE PLC

Inventor： Robert E Christie ,  David G MacManus ,  Christopher T J Sheaf

IPC: F02C7/04 ,  F02K3/068 ,  B64D33/02

Abstract: A nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake disposed at an upstream end of the nacelle. The air intake includes, in flow series, an intake lip, a throat and a diffuser. The diffuser further includes a diffuser angle (θdiff), indicating a degree of divergence of the diffuser relative to the longitudinal centre line. The diffuser angle (θdiff) is from about 0 degrees to about 12 degrees.

公开(公告)号：US11480073B2

公开(公告)日：2022-10-25

申请号：US17518081

申请日：2021-11-03

Applicant: Rolls-Royce plc

Inventor： Robert E. Christie ,  David G. MacManus ,  Christopher T J Sheaf

IPC: F02C7/04 ,  F01D25/24 ,  B64D29/00

Abstract: A system and a method of designing a nacelle for a gas turbine engine having a longitudinal centre line. The nacelle includes an air intake, an internal surface, an azimuthal angle, and a plurality of intake lines. The air intake comprises, in flow series, an intake lip, a throat and a diffuser. The internal surface at least partially defines the air intake. The azimuthal angle is defined about the longitudinal centre line. The intake lines extend along the internal surface of the nacelle at respective values of the azimuthal angle. Each intake line axially defines the air intake along the longitudinal centre line at the respective value of the azimuthal angle. The internal surface of the nacelle between the plurality of intake lines at a given axial location along the longitudinal centre line is analytically defined by an equation.

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.