公开(公告)号：US20200378274A1

公开(公告)日：2020-12-03

申请号：US16941754

申请日：2020-07-29

Applicant: ROLLS-ROYCE plc

Inventor： Christopher Richard HALLAM ,  Jonathan Paul TAYLOR

IPC: F01D25/28 ,  B64F5/50 ,  F02C7/20 ,  B23P19/04 ,  F16M11/42

Abstract: A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.

公开(公告)号：US20150135535A1

公开(公告)日：2015-05-21

申请号：US14527072

申请日：2014-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Richard HALLAM ,  Jonathan Paul TAYLOR

IPC: F01D25/28 ,  F16M11/42 ,  B23P19/04

CPC classification number: F01D25/285 ,  B23P19/04 ,  B64F5/50 ,  F02C7/20 ,  F16M11/42 ,  Y10T29/49318 ,  Y10T29/49721 ,  Y10T29/49895

Abstract: A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44). The fan case frame (44) further comprising a coupling arrangement (56) arranged to rotate about a roll axis (60) and to couple a fan case (36) to the fan case frame (44). A gas turbine engine stand assembly (68) comprising a fan stand (40) and a core stand (38). A method of splitting a gas turbine engine (10) and a method of reassembling a gas turbine engine (10).

Abstract translation: 一种燃气涡轮发动机风扇支架（40），包括基座框架（42）和风扇壳体框架（44），其通过铰链（46）在一个边缘处联接在一起。 风扇壳体框架（44）被布置成：在邻接基座框架（42）并且基本垂直于其之间围绕铰链（46）旋转; 并且围绕垂直于铰链（46）并在风扇壳体框架（44）的平面内的偏转轴线（52）倾斜。 风扇壳体框架（44）还包括联接装置（56），其布置成围绕辊轴线（60）旋转并将风扇壳体（36）联接到风扇壳体框架（44）。 一种燃气涡轮发动机支架组件（68），包括风扇支架（40）和芯架（38）。 一种分解燃气涡轮发动机（10）的方法和重新组装燃气涡轮发动机（10）的方法。

公开(公告)号：US20150136935A1

公开(公告)日：2015-05-21

申请号：US14527002

申请日：2014-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher Richard HALLAM ,  Jonathan Paul TAYLOR

IPC: F02C7/20

CPC classification number: F02C7/20 ,  B64F5/50 ,  F01D25/285 ,  F05D2220/32 ,  F05D2260/02 ,  G01M15/02 ,  G01M15/14

Abstract: A gas turbine engine stand (38) comprising an engine frame (48) and a base frame (46). The base frame (46) has a slide rail (51) to enable axial translation of the engine frame (48) relative to the base frame (46). A load transfer arrangement (54) engages with a part (50) of the engine frame (48) and slidingly engages with the slide rail (51). There is a locking mechanism (62) to lock the engine frame (48) to the base frame (46) to prevent relative axial translation. The gas turbine engine stand (38) is used, inter alia, for splitting a core engine (34) from a fan case (36).

Abstract translation: 一种燃气涡轮发动机支架（38），包括发动机框架（48）和基座框架（46）。 底架（46）具有滑轨（51），以使发动机框架（48）相对于基架（46）能够轴向平移。 负载传递装置（54）与发动机框架（48）的一部分（50）接合并且滑动地与滑轨（51）接合。 存在将发动机框架（48）锁定到基座框架（46）的锁定机构（62），以防止相对的轴向平移。 特别地，燃气涡轮发动机支架（38）用于从风扇壳体（36）分离芯发动机（34）。