公开(公告)号：US20190249720A1

公开(公告)日：2019-08-15

申请号：US16249187

申请日：2019-01-16

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. MAGUIRE

IPC: F16D3/50 ,  F02C7/36 ,  F02C3/04 ,  F02K3/06 ,  F16C3/02 ,  F16D3/06

CPC classification number: F16D3/50 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2240/61 ,  F05D2240/62 ,  F16C3/02 ,  F16D3/06

Abstract: A turbofan engine driveshaft comprises, in axial sequence along an axial centreline, a driving portion, and a driven portion. The driving portion has a first end and a second end. The second end of driving portion is connected to the driven portion. The driven portion comprises an annular drum having a radially inwardly facing surface, with the annular drum having a stiffener attached to the radially inwardly facing surface.The driveshaft is supported radially by a bearing assembly at the connection between the driving portion and the driven portion. The driving portion is configured to accommodate a predetermined range of movement of the outer end relative to the inner end.

公开(公告)号：US20170191413A1

公开(公告)日：2017-07-06

申请号：US15372289

申请日：2016-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A. KNIGHT ,  Alan R. MAGUIRE ,  Daniel ROBINSON ,  George BOSTOCK ,  Christopher T. J. SHEAF

IPC: F02C6/08 ,  B64D27/10 ,  B64D13/02 ,  F02C7/36 ,  F02C7/04

CPC classification number: F02C6/08 ,  B64D13/02 ,  B64D27/10 ,  F02C7/04 ,  F02C7/057 ,  F02C7/277 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2270/102 ,  F05D2270/1022 ,  Y02T50/671

Abstract: A gas turbine engine including an intake, a fan and an injector system. The intake has an inner wall which defines an intake passage for the fan. The injector system includes a cabin blower system including a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and by the injector system. The intake includes an injector of the injector system through which in use fluid from the cabin blower compressor is injected into a main airflow for flow control of air on the way to the fan.

公开(公告)号：US20160341215A1

公开(公告)日：2016-11-24

申请号：US15136409

申请日：2016-04-22

Applicant: ROLLS-ROYCE plc

Inventor： Glenn A. KNIGHT ,  Alan R. MAGUIRE ,  Daniel ROBINSON ,  George BOSTOCK ,  Mark J. WILSON

IPC: F04D29/52 ,  B64D13/06 ,  F04D27/00 ,  F04D19/00 ,  F04D29/32

CPC classification number: F04D29/526 ,  B64C21/04 ,  B64D13/02 ,  B64D13/04 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2033/0286 ,  F04D19/00 ,  F04D25/02 ,  F04D25/028 ,  F04D27/009 ,  F04D27/0261 ,  F04D29/324 ,  F04D29/684 ,  F05D2220/36 ,  F05D2270/101 ,  F16H15/38 ,  F16H37/084 ,  F16H37/086 ,  F16H2037/088

Abstract: A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.

Abstract translation: 公开了一种燃气涡轮发动机，其包括压缩机，围绕压缩机的压缩机壳体和压缩机尖端喷射器系统。 压缩机叶尖喷射器系统包括舱室鼓风机系统，其包括在使用中布置的用于压缩在飞机的舱室中使用的空气和由压缩机叶尖喷射器系统布置的舱室鼓风机压缩机。 压缩机壳体包括一个或多个压缩机尖端喷射器系统的喷射器，在使用时，来自机舱鼓风机压缩机的空气在压缩机旋转时被喷射到压缩机的叶片的叶片末端。