公开(公告)号：US20210355843A1

公开(公告)日：2021-11-18

申请号：US17231460

申请日：2021-04-15

Applicant: ROLLS-ROYCE plc

Inventor： Fernando L. TEJERO EMBUENA ,  David G. MACMANUS ,  Christopher TJ. SHEAF

IPC: F01D25/24

Abstract: A nacelle for a gas turbine engine includes a leading edge, a trailing edge and a longitudinal centre line along a length of the nacelle. A highlight radius (rhi) is defined as a radial distance between the longitudinal centre line and the leading edge. A trailing edge radius (rte) is defined as a radial distance between the longitudinal centre line and the trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. A ratio between the nacelle length (Lnac) and the highlight radius (rhi) is defined as R1 (Lnac/rhi). The ratio R1 is greater than or equal to 2.4 and less than or equal to 3.2. A ratio between the trailing edge radius (rte) and the highlight radius (rhi) is defined as R2. The ratio R2 is greater than or equal to 0.89 and less than or equal to 1.

公开(公告)号：US20210164356A1

公开(公告)日：2021-06-03

申请号：US17084821

申请日：2020-10-30

Applicant: ROLLS-ROYCE plc

Inventor： Fernando L. TEJERO EMBUENA ,  David G. MACMANUS ,  Christopher TJ SHEAF

IPC: F01D9/04 ,  F01D25/24 ,  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.

公开(公告)号：US20210381397A1

公开(公告)日：2021-12-09

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：US20210355872A1

公开(公告)日：2021-11-18

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

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：US20210254507A1

公开(公告)日：2021-08-19

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：US20170167295A1

公开(公告)日：2017-06-15

申请号：US15361234

申请日：2016-11-25

Applicant: ROLLS-ROYCE, PLC

Inventor： Angus R. SMITH ,  Christopher T. SHEAF ,  David G. MACMANUS

IPC: F01D25/24 ,  F02C7/04 ,  F01D25/04 ,  F01D9/02 ,  F04D29/52 ,  F04D29/66

CPC classification number: F01D25/24 ,  B64D33/02 ,  B64D2033/0226 ,  F01D9/02 ,  F01D25/04 ,  F02C7/04 ,  F04D29/526 ,  F04D29/664 ,  F05D2220/323 ,  F05D2270/17 ,  Y02T50/671

Abstract: A nacelle for a turbofan gas turbine engine, having in flow series an intake lip, a diffuser and a fan casing. The diffuser has, in flow series, a main section and a recessed section adjacent to the fan casing. A transition region, such as a step, slope or curve, is provided between the main section and the recessed section. In some arrangements the transition region may be configured to promote flow separation and the formation of a separation bubble in the recessed section.