公开(公告)号：US20200157946A1

公开(公告)日：2020-05-21

申请号：US16672662

申请日：2019-11-04

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. GOODHAND

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

Abstract: 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：US20200156767A1

公开(公告)日：2020-05-21

申请号：US16672580

申请日：2019-11-04

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. GOODHAND

IPC: B64C21/06 ,  B64C7/02

Abstract: 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 ϵ [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：US20200063607A1

公开(公告)日：2020-02-27

申请号：US16283353

申请日：2019-02-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. GOODHAND ,  Ian M. BUNCE

IPC: F01K25/10 ,  F04D7/02 ,  F04D29/22

Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203).

公开(公告)号：US20200063566A1

公开(公告)日：2020-02-27

申请号：US16282976

申请日：2019-02-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. GOODHAND ,  Ian M. BUNCE

IPC: F01D5/14

Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203). The radius of the inlet (r0) is from 25 to 50 percent of the radius of the impeller (r2).

公开(公告)号：US20180237126A1

公开(公告)日：2018-08-23

申请号：US15899481

申请日：2018-02-20

Applicant: ROLLS-ROYCE plc

Inventor： Martin N. GOODHAND ,  Matthew MOXON

IPC: B64C21/06 ,  B64C11/18

Abstract: 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.