公开(公告)号：US20180274443A1

公开(公告)日：2018-09-27

申请号：US15928498

申请日：2018-03-22

Applicant: ROLLS-ROYCE plc

Inventor： James M. POINTON ,  Stephen J. BRADBROOK

IPC: F02C7/06 ,  F02K3/06 ,  F01D25/16 ,  F01D25/24 ,  F01D25/28

CPC classification number: F02C7/06 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02K3/06 ,  F05D2220/3215 ,  F05D2220/323 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2240/52 ,  F05D2240/61 ,  F05D2240/62 ,  F05D2260/40311 ,  F05D2260/941 ,  Y02T50/671

Abstract: An aircraft gas turbine engine comprises a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, and a low pressure compressor coupled to a low pressure turbine by a low pressure shaft. The engine includes a first shaft bearing configured to support a forward end of the low pressure shaft, the first shaft bearing being mounted to a static structure forward of the high pressure turbine. The engine also includes a second shaft bearing configured to support a rearward end of the low pressure shaft, the second shaft bearing being mounted to a static structure rearward of the high pressure turbine, and forward of the low pressure turbine. The engine further includes a third shaft bearing configured to support the low pressure shaft, the third shaft bearing being mounted to a static structure rearward of the low pressure turbine.

公开(公告)号：US20180252166A1

公开(公告)日：2018-09-06

申请号：US15912778

申请日：2018-03-06

Applicant: ROLLS-ROYCE plc

Inventor： James M. POINTON ,  Stephen J. BRADBROOK

IPC: F02C7/36 ,  F16H1/28 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F16H1/28

Abstract: A gas turbine engine (10) comprising: a low pressure turbine (19); a fan (13) drivable by the low pressure turbine. A high pressure turbine (18) and a high pressure compressor (16) coupled by a high pressure shaft (24). An epicyclic gearbox (14) in planetary configuration coupled between a low pressure shaft (23) and the fan. The engine having a bypass ratio greater than or equal to 13. Or the fan having a diameter greater than or equal to 85 inches and less than or equal to 170 inches. Or the engine arranged to generate thrust in the range 35,000 lbf to 130,000 lbf.