公开(公告)号：US10598048B2

公开(公告)日：2020-03-24

申请号：US15954746

申请日：2018-04-17

Applicant: ROLLS-ROYCE plc

Inventor： Michael P. Keenan ,  Stewart T. Thornton

IPC: F01D25/36 ,  F01D15/10 ,  F02C7/18

Abstract: There is disclosed an auxiliary rotation device 28 for a gas turbine engine 10. The auxiliary rotation device 28 comprises: an electric machine 30 configured to be coupled to a rotor of the gas turbine engine 10; and a dedicated electrical storage device 32 coupled to the electric machine 30. During a period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a generator so as to charge the dedicated electrical storage device 32. Following the period of powered operation of the gas turbine engine 10 the electric machine 30 is configured to act as a motor by discharging the dedicated electrical storage device 32 so as to cause the rotor to rotate for a period of time to provide even cooling of the rotor around its circumference. There is also disclosed a method of cooling a rotor of a gas turbine engine 10 using an auxiliary rotation device 28.

公开(公告)号：US11230945B2

公开(公告)日：2022-01-25

申请号：US16720068

申请日：2019-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. Maguire ,  Stewart T. Thornton ,  Philip C. Bond ,  Glenn A. Knight

IPC: F01D25/16 ,  F02C7/06

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.

公开(公告)号：US10830151B2

公开(公告)日：2020-11-10

申请号：US16410312

申请日：2019-05-13

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Swift ,  Stewart T. Thornton

IPC: F02C7/32 ,  F16H57/021 ,  F16H57/023 ,  F02K3/06

Abstract: A coupling arrangement for a gas turbine engine. The arrangement comprises first, second and third members. The first member has a first threaded mating surface extending in a first direction (X) and a flange extending in a direction generally normal to the first direction (X). The second member has a second threaded mating surface extending in the first direction (X) and a flange extending in a direction generally normal to the first direction (X), the flanges of the first and second members engaging against one another. The third member has a third threaded mating surface configured to engage against the first threaded mating surface, and a fourth threaded mating surface configured to engage against the second threaded mating surface.

公开(公告)号：US10294872B2

公开(公告)日：2019-05-21

申请号：US15661458

申请日：2017-07-27

Applicant: ROLLS-ROYCE plc

Inventor： Stewart T. Thornton ,  Andrew Swift

IPC: F02C7/36 ,  F16H57/00 ,  F02K3/06 ,  F16C1/02 ,  F16D3/76 ,  F16H1/28

Abstract: Disclosed is a gas turbine engine comprising: 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 the sun gear is driveably connected to the low pressure shaft, and either of carrier and ring gear provides an output drive connected to a propulsive fan; wherein the connection between the low pressure shaft and the sun gear includes a flexible drive shaft having serially connected concentrically nested first and second input shafts between the low pressure shaft and sun gear.