公开(公告)号：US20180030901A1

公开(公告)日：2018-02-01

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 ,  F16D3/76 ,  F16H1/28 ,  F02K3/06 ,  F16C1/02

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2240/40 ,  F05D2240/61 ,  F05D2240/62 ,  F05D2260/40311 ,  F16C1/02 ,  F16D3/76 ,  F16H1/28 ,  F16H57/0025

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.

公开(公告)号：US20200347748A1

公开(公告)日：2020-11-05

申请号：US16451537

申请日：2019-06-25

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K. KANNANGARA ,  Jillian C. GASKELL ,  Stewart T. THORNTON ,  Timothy PHILP

IPC: F01D25/24 ,  F01D15/12

Abstract: A gas turbine engine for an aircraft and an engine core including: a compressor system, a first lower pressure compressor, a second, higher pressure compressor; an outer core casing surrounding the compressor system. The outer core casing includes a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, the first flange connection having a first flange radius, wherein the first flange connection is the connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor, and a front mount arranged to be connected to a pylon. A front mount position ratio of: axial   distance   between   the   first   flange   connection and   the   front   mount first   flange   radius is equal to or less than 1.18.

公开(公告)号：US20200347731A1

公开(公告)日：2020-11-05

申请号：US16778795

申请日：2020-01-31

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K. KANNANGARA ,  Jillian C. GASKELL ,  Stewart T. THORNTON ,  Timothy PHILP

IPC: F01D5/14 ,  F02C7/36 ,  F02K3/06 ,  F01D25/28 ,  F16H1/28 ,  F01D25/24

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing. The engine includes a front mount arranged for connection to a pylon; and a fan located upstream of the engine core. The outer core casing includes a first flange connection that: is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A front mount position ratio of: axial   distance   between   the   first   flange   connection and   the   front   mount first   flange   radius is equal to or less than 1.18.

公开(公告)号：US20200347742A1

公开(公告)日：2020-11-05

申请号：US16520740

申请日：2019-07-24

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K. KANNANGARA ,  Jillian C. GASKELL ,  Stewart T. THORNTON ,  Timothy PHILP

IPC: F01D13/00 ,  F01D5/12 ,  F01D5/30

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure, compressor, and a second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, wherein the first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor; a nacelle surrounding the engine core and defining a bypass duct between the engine core and the nacelle; wherein an axial midpoint of the radially outer edge is defined as the fan OGV tip centrepoint.

公开(公告)号：US20190218978A1

公开(公告)日：2019-07-18

申请号：US16233526

申请日：2018-12-27

Applicant: ROLLS-ROYCE plc

Inventor： David A. EDWARDS ,  Stewart T. THORNTON

IPC: F02C7/32 ,  F02C7/268 ,  F16H57/038

CPC classification number: F02C7/32 ,  F02C7/268 ,  F05D2220/50 ,  F05D2220/76 ,  F05D2260/4031 ,  F05D2260/53 ,  F05D2260/532 ,  F05D2260/85 ,  F16H57/038 ,  F16H2057/02026 ,  F16H2057/02039

Abstract: A gas turbine engine accessory gearbox assembly comprising an accessory gearbox and a plurality of accessories arranged to be driven by the accessory gearbox. The accessory gearbox comprises a gear train and an accessory gearbox casing enclosing the gears of the gear train. Each accessory is driven by a shaft and the shaft of each accessory has a spur gear. The gear train comprises the spur gears of the accessories. The shaft of at least one of the accessories has a bevel gear and the bevel gear is arranged to mesh with a further bevel gear and the further bevel gear is arranged to drive the accessory gearbox assembly. The accessories may be arranged in V-shape on the core engine casing within an aerodynamic core nacelle.

公开(公告)号：US20180306065A1

公开(公告)日：2018-10-25

申请号：US15954746

申请日：2018-04-17

Applicant: ROLLS-ROYCE plc

Inventor： Michael P. KEENAN ,  Stewart T. THORNTON

IPC: F01D25/36 ,  F02C7/18

CPC classification number: F01D25/36 ,  F01D15/10 ,  F02C7/18 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/221 ,  F05D2260/42

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：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.

公开(公告)号：US20200347730A1

公开(公告)日：2020-11-05

申请号：US16778617

申请日：2020-01-31

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K. KANNANGARA ,  Jillian C. GASKELL ,  Stewart T. THORNTON ,  Timothy PHILP

IPC: F01D5/14 ,  F02C7/36 ,  F02K3/06 ,  F16H1/28 ,  F01D25/28 ,  F01D25/24

Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and inner and outer core casings that define a core working gas flow path (A) therebetween, which has an outer radius that defines a gas path radius. The outer core casing includes a first flange connection that: has a first flange radius, is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A gas path ratio of: first   flange   radius gas   path   radius is equal to or greater than 1.10.

公开(公告)号：US20200224554A1

公开(公告)日：2020-07-16

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

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：US20190360403A1

公开(公告)日：2019-11-28

申请号：US16410312

申请日：2019-05-13

Applicant: ROLLS-ROYCE plc

Inventor： Andrew SWIFT ,  Stewart T. THORNTON

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

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.