公开(公告)号：US20170081973A1

公开(公告)日：2017-03-23

申请号：US15262993

申请日：2016-09-12

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew SWIFT ,  Stewart T THORNTON ,  Paul SIMMS ,  Glenn A. KNIGHT

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/32 ,  F01D5/02

CPC classification number: F01D15/12 ,  F01D5/02 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2240/62 ,  F05D2250/232 ,  F05D2250/311 ,  F05D2260/40311 ,  F05D2260/941 ,  F05D2260/96 ,  F16H1/28 ,  Y02T50/671

Abstract: A gas turbine engine, including: low pressure spool having low pressure compressor and low pressure turbine connected by low pressure shaft; reduction gear train having sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft connected to the output drive of the gear train via a coupling, wherein the coupling includes a connection point to the fan shaft at a first end, and a connection point to the gear train at a second end wherein the first and second end are axial separated and radially separated and the axial separation is greater than the radial separation.

公开(公告)号：US20200003129A1

公开(公告)日：2020-01-02

申请号：US16453141

申请日：2019-06-26

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

Inventor： Dominic BONIFACE ,  Andrew SWIFT ,  Stewart THORNTON ,  Paul SIMMS ,  Glenn KNIGHT ,  Geoff HUGHES

IPC: F02C7/36 ,  F02K3/06 ,  F02C7/06 ,  F02C3/107 ,  F01D25/16

Abstract: The invention relates to a gas turbine engine, in particular an aircraft engine, comprising: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.

公开(公告)号：US20170082065A1

公开(公告)日：2017-03-23

申请号：US15262612

申请日：2016-09-12

Applicant: ROLLS-ROYCE plc

Inventor： Andrew SWIFT ,  Stewart T. THORNTON ,  Paul SIMMS ,  Glenn A. KNIGHT

IPC: F02K3/06 ,  F02C7/36 ,  F01D25/16

CPC classification number: F02K3/06 ,  F01D25/16 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/32 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2250/311 ,  F05D2260/40311 ,  F05D2260/941 ,  F05D2260/96

Abstract: A gas turbine engine, including: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein one of the sun gear, carrier or ring gear is connected to the low pressure shaft, and another of the sun gear, carrier and ring gear provides an output drive; a propulsive fan mounted fore of the gear train; a fan shafting arrangement comprising a fan shaft which is connected to the output drive of the gear train and a fan support shaft which passes through centre of the gear train along the axis of rotation of the gearbox and fan, wherein the fan shafting arrangement is rotatably supported by at least two axially separated bearings.