公开(公告)号：US11486254B2

公开(公告)日：2022-11-01

申请号：US16672662

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： F01D5/14 ,  F04D29/32 ,  F04D29/38

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r∈[rhub, rtip]). A plurality of outlet guide vanes are positioned aft of the fan. An afterbody is located aft of the plurality of outlet guide vanes and which tapers to an apex having an apex angle with respect to the rotational axis of between 35 and 45 degrees.

公开(公告)号：US11414178B2

公开(公告)日：2022-08-16

申请号：US16672606

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： B64C21/06 ,  F01D5/14

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub. A blade blockage, which is the ratio of the blade thickness to the product of the circumferential pitch and the cosine of a blade inlet angle (t/s·cosβ1), is 0.25 or greater at the 0 percent span position.

公开(公告)号：US11365633B2

公开(公告)日：2022-06-21

申请号：US16672591

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： F01D5/14 ,  F04D29/32 ,  F04D29/38

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft includes a nacelle (501) defining a duct (502), and a fan (503) located therewithin. The fan comprises a hub which rotates around a rotational axis (A-A) and a plurality of blades attached thereto. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r∈[0, 1]), a leading edge and a trailing edge defining, for each span position, a chord therebetween having a chord length (c), and a blade thickness (t) defined for each span position thereof. For each blade, a ratio of thickness at the 0 percent span position (thub) to chord length is 0.1 or greater.

公开(公告)号：US11364996B2

公开(公告)日：2022-06-21

申请号：US16672580

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： B64C21/06 ,  B64C7/02

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct (502), and a fan (503) located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r ∈ [0, 1]), and a stagger angle at the 0 percent span position (ζhub) relative to the rotational axis of 40 degrees or greater.

公开(公告)号：US11486253B2

公开(公告)日：2022-11-01

申请号：US16672648

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： F01D5/14 ,  F04D29/32 ,  F04D29/38

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r∈[rhub, rtip]). The hub has a negative hade angle (γ) with respect to the rotational axis at an axial position coincident with the leading edge of the blades.

公开(公告)号：US11370530B2

公开(公告)日：2022-06-28

申请号：US16672584

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： B64C21/06 ,  B64C7/02

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct, and a fan located therewithin. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached thereto. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r ∈ [0, 1]), and leading and trailing edges defining, for each span position, a chord therebetween to having a chord length (c). For each of said plurality of blades, the ratio of chord length at the 0 percent span position (chub) to chord length at the 100 percent span position (ctip) is 1 or greater.

公开(公告)号：US11365634B2

公开(公告)日：2022-06-21

申请号：US16672636

申请日：2019-11-04

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand

IPC分类号： F01D5/14 ,  F04D29/32 ,  F04D29/38

摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r∈[rhub, rtip]). A hub-tip ratio of the fan, defined as the ratio of the diameter of the hub to the diameter of the fan measured at the leading edge of the blades, is from 0.45 to 0.55.

公开(公告)号：US10787270B2

公开(公告)日：2020-09-29

申请号：US15899481

申请日：2018-02-20

申请人： ROLLS-ROYCE plc

发明人： Martin N. Goodhand ,  Matthew Moxon

IPC分类号： B64D27/02 ,  B64C11/18 ,  B64C11/48 ,  B64C21/00

摘要： A boundary layer propulsor comprises a rotor and a plurality of first aerofoil blades. The rotor has an axis of rotation. The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion, a middle portion, and a radially distal portion. The radially proximal portion has a first cambered cross-section, the middle portion has a second uncambered cross-section, and the radially distal portion has a third cambered cross-section. The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section.