公开(公告)号：US11292605B2

公开(公告)日：2022-04-05

申请号：US16396923

申请日：2019-04-29

Applicant: ROLLS-ROYCE plc

Inventor： Joseph B. Cooper

IPC: B64D27/26 ,  F01D25/28 ,  F02C7/20 ,  F02C7/268

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.

公开(公告)号：US10907476B2

公开(公告)日：2021-02-02

申请号：US16374778

申请日：2019-04-04

Applicant: ROLLS-ROYCE plc

Inventor： Joseph B. Cooper

IPC: F01D5/02 ,  F02K3/06 ,  F16D1/05

Abstract: A shaft assembly for a gas turbine engine is provided. The shaft assembly comprises: a first shaft having an outer surface; a first coupling ring disposed around the outer surface of the first shaft, an inner surface of the first coupling ring being coupled to the outer surface of the first shaft; a second shaft having an inner surface; and a second coupling ring disposed around the inner surface of the second shaft, an outer surface of the second coupling ring being coupled to the inner surface of the second shaft, wherein an outer surface of the first coupling ring is configured to mate with an inner surface of the second coupling ring, such that concentricity of the first and second shafts is maintained at the shaft assembly by virtue of the mating of the first and second coupling rings. Methods of assembling and re-assembling a shaft assembly are also provided.

公开(公告)号：US11254447B2

公开(公告)日：2022-02-22

申请号：US16407794

申请日：2019-05-09

Applicant: ROLLS-ROYCE plc

Inventor： Joseph B. Cooper

IPC: B64F5/10 ,  B64D27/12 ,  B64D27/26 ,  B64D35/02

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. At least one temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link each comprise a respective winch operable to adjust pay out of a respective tension member thereby to provide length adjustment. The temporary forward link and the temporary rearward link maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.