公开(公告)号：US09683488B2

公开(公告)日：2017-06-20

申请号：US14137453

申请日：2013-12-20

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce PLC

Inventor： Robert A. Ress, Jr. ,  Andrew Swift

IPC: F01D9/02 ,  F02C3/08 ,  F04D29/44 ,  F04D29/62 ,  F01D11/00 ,  F04D29/16

CPC classification number: F02C3/08 ,  F01D11/005 ,  F04D29/162 ,  F04D29/444 ,  F04D29/624 ,  F05D2240/12 ,  F05D2240/581 ,  Y10T29/49243

Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

公开(公告)号：US11066959B2

公开(公告)日：2021-07-20

申请号：US16453100

申请日：2019-06-26

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Swift

IPC: F01D25/28 ,  B64D27/12 ,  B64D29/02 ,  B64D29/06 ,  F01D25/24 ,  F02C7/36 ,  B64D33/02 ,  B64D33/04

Abstract: An aircraft gas turbine engine includes an engine core including a turbine, a compressor, a core shaft connecting the turbine to compressor, and a core casing surrounding the engine core. A fan is located upstream of the engine core and fan casing surrounds the fan. A gearbox receives input from the core shaft and outputs drive to rotate the fan. A single plane support structure connects the core and fan casing. The support structure includes an inner ring, outer ring and plurality of circumferentially spaced radially extending struts connecting the inner and outer ring. The inner ring including a torsion box and a gearbox and fan support structure is connected to the torsion box. A front and rear mount are configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to the torque box and the rear mount is coupled to the core casing.

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：US10393068B2

公开(公告)日：2019-08-27

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 ,  F01D25/16 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36

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 center 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：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.

公开(公告)号：US20140248142A1

公开(公告)日：2014-09-04

申请号：US14137453

申请日：2013-12-20

Applicant: Rolls-Royce PLC ,  Rolls-Royce North American Technologies, Inc.

Inventor： Robert A. Ress, JR. ,  Andrew Swift

IPC: F01D9/02

CPC classification number: F02C3/08 ,  F01D11/005 ,  F04D29/162 ,  F04D29/444 ,  F04D29/624 ,  F05D2240/12 ,  F05D2240/581 ,  Y10T29/49243

Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

Abstract translation: 燃气涡轮发动机包括旋转地联接到轴的压缩机组件，压缩机组件具有离心式叶轮和覆盖离心式叶轮的叶片部分的护罩。 压缩机组件包括经由一对凸缘附接到护罩的扩散器，扩散器包括通过后延伸的腿安装到室内基座的支柱。 密封组件附接到扩散器并且可附接到过渡管道，该过渡管道定位成从扩散器接收空气。 密封组件被构造成防止空气通过密封组件，同时允许在过渡管道和扩散器之间发生相对运动。