公开(公告)号：US11371467B2

公开(公告)日：2022-06-28

申请号：US16528201

申请日：2019-07-31

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F02K3/06 ,  B64D27/16

Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The inner fan is configured to have, in operation, a tip speed of from 1 to 3 times that of the outer fan.

公开(公告)号：US11247780B2

公开(公告)日：2022-02-15

申请号：US16528034

申请日：2019-07-31

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: B64D27/24 ,  F02K5/00 ,  F02K3/072 ,  B64C11/48 ,  B64C11/00 ,  F02K3/06 ,  F02C7/36 ,  F02C6/00 ,  B64D35/06 ,  F02K3/077 ,  F04D19/00 ,  F04D25/06 ,  B64D27/02

Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. A hub-tip ratio of the outer fan is from 1.6 to 2.2 times a hub-tip ratio of the inner fan.

公开(公告)号：US11891184B2

公开(公告)日：2024-02-06

申请号：US17098758

申请日：2020-11-16

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Gideon Daniel Venter ,  Giles E Harvey

IPC: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C6/20 ,  F02C7/36 ,  H02K7/108 ,  H02K7/116 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  F16D7/00 ,  F16H57/02

CPC classification number: B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C6/20 ,  F02C7/36 ,  H02K7/108 ,  H02K7/116 ,  H02K7/1823 ,  H02K7/20 ,  H02K11/0094 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2220/76 ,  F16D7/007 ,  F16H57/02 ,  F16H2057/02043

Abstract: An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and electric machine rotor (78) to the propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).

公开(公告)号：US11761448B2

公开(公告)日：2023-09-19

申请号：US16395996

申请日：2019-04-26

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F04D25/06 ,  B64D27/24 ,  B64D35/02

CPC classification number: F04D25/06 ,  B64D27/24 ,  B64D35/02

Abstract: The present disclosure concerns an electric aircraft propulsion system. Example embodiments include an aircraft propulsion system (200) comprising: a fan (213) mounted on a central shaft (214); a first electric motor (215) mounted on the central shaft (214) and arranged to drive rotation of the fan (213) via the central shaft; and a second electric motor (216) arranged to drive rotation of the fan (213) via the central shaft (214), wherein the second electric motor (216) is coaxially mounted downstream of the first electric motor (215) and an outer diameter (D2) of the second electric motor (216) is smaller than an outer diameter (D1) of the first electric motor (215).

公开(公告)号：US11313327B2

公开(公告)日：2022-04-26

申请号：US16528114

申请日：2019-07-31

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F02K3/072

Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The outer fan has a diameter of from 2.5 to 3.5 times a diameter of the inner fan.

公开(公告)号：US10955045B2

公开(公告)日：2021-03-23

申请号：US16702716

申请日：2019-12-04

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F16H57/08 ,  F02C7/36

Abstract: A planet carrier for an epicyclic gearbox, the planet carrier comprising: a single piece carrier body arranged to support a plurality of gears of the epicyclic gearbox; and an opening in a wall of the carrier body; wherein: in a cross-section of the carrier body in a plane that is orthogonal to the longitudinal axis of the carrier body and at a longitudinal position along the carrier body that does not comprise the opening, the carrier body is substantially annular; and the opening is arranged such that the gears that the carrier body is arranged to support can be passed entirely through the opening.

公开(公告)号：US11313440B2

公开(公告)日：2022-04-26

申请号：US16655605

申请日：2019-10-17

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F16H1/36 ,  F02C7/32 ,  F02C7/36

Abstract: A star-configuration epicyclic gearbox is shown. It comprises a sun gear (112) for connection with a first shaft (112), a plurality of planet gears (113) intermeshed with the sun gear and located in a static carrier (114), and a ring gear (115) for connection with a second shaft (116) and which is intermeshed with the plurality of planet gears. It further comprises one or more electric machines (117) drivingly connected with a respective one of the plurality of planet gears.

公开(公告)号：US11306682B2

公开(公告)日：2022-04-19

申请号：US16527905

申请日：2019-07-31

Applicant: ROLLS-ROYCE plc

Inventor： Giles E Harvey

IPC: F02K3/072

Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. A swept area of the outer fan is from 2 to 20 times greater than a swept area of the inner fan.