公开(公告)号：US09757918B2

公开(公告)日：2017-09-12

申请号：US14196751

申请日：2014-03-04

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Hillier

IPC: B32B5/02 ,  B32B18/00 ,  C04B26/04 ,  C04B30/02 ,  B28B1/00 ,  B28B3/02 ,  B28B23/00

CPC classification number: B32B5/02 ,  B28B1/008 ,  B28B3/021 ,  B28B23/0006 ,  B32B18/00 ,  B32B2262/105 ,  C04B26/04 ,  C04B30/02 ,  C04B2237/38 ,  C04B2237/64 ,  C04B2237/76 ,  Y10T428/24628 ,  Y10T428/24669 ,  C04B14/06 ,  C04B14/303 ,  C04B14/46 ,  C04B38/067 ,  C04B40/0268

Abstract: The invention concerns an article (20) formed of a ceramic matrix composite structure having a plurality of ceramic fiber layers (22) and a binder material (24) interspersed throughout said layers. The ceramic matrix composite material may be sintered. The ceramic fiber layers undulate relative to one or more outer surfaces (38;40) of the article. Thus support features (48) within the article are able to share a load in use between a plurality of layers. The invention may be suited to engine components such as turbine seal segments in a gas turbine engine.

公开(公告)号：US20170145845A1

公开(公告)日：2017-05-25

申请号：US14950794

申请日：2015-11-24

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

Inventor： Daniel K. Vetters ,  Peter Broadhead ,  Steven Hillier

IPC: F01D9/06 ,  F01D11/08 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D9/06 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/676

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

公开(公告)号：US12228044B1

公开(公告)日：2025-02-18

申请号：US18755463

申请日：2024-06-26

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： David J. Thomas ,  Ted J. Freeman ,  Aaron D. Sippel ,  Clark J. Snyder ,  Steven Hillier

IPC: F01D11/08 ,  F01D25/24

Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall. The second shroud segment includes a second carrier segment and a second blade track. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

公开(公告)号：US11002143B2

公开(公告)日：2021-05-11

申请号：US16136866

申请日：2018-09-20

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

Inventor： Daniel K. Vetters ,  Peter Broadhead ,  Steven Hillier

IPC: F01D25/12 ,  F01D9/06 ,  F01D9/02 ,  F01D11/08

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

公开(公告)号：US20200340883A1

公开(公告)日：2020-10-29

申请号：US16394648

申请日：2019-04-25

Applicant: Rolls-Royce plc

Inventor： Alexander Wong ,  Steven Hillier ,  Michael J. Whittle

IPC: G01M15/14 ,  H04N5/33 ,  G01N25/72 ,  G01J5/00 ,  G01J5/08 ,  G01J5/06

Abstract: According to an aspect of this disclosure, a system of applying thermal loads may include at least one laser module, and a plurality of optical components fixed to the at least one laser module and directing a plurality of laser beams from the plurality of optical components towards a surface. Further, the plurality of laser beams apply radiative heating to the surface in accordance with the system. The system also includes at least one infrared camera measuring thermal conditions of the surface, and a controller coordinating operation of the at least one laser module and the at least one infrared camera.

公开(公告)号：US20200263557A1

公开(公告)日：2020-08-20

申请号：US16279469

申请日：2019-02-19

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Steven Hillier

IPC: F01D9/06 ,  F01D25/12

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.

公开(公告)号：US10393026B2

公开(公告)日：2019-08-27

申请号：US15442192

申请日：2017-02-24

Applicant: ROLLS-ROYCE plc

Inventor： Steven Hillier

IPC: F01D25/16 ,  F02C7/28 ,  F01D11/08 ,  F01D25/12 ,  F01D25/24 ,  F01D5/22 ,  F01D11/00

Abstract: This disclosure describes a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts the either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes axially compressible segments which allow the seal member to bend longitudinally.

公开(公告)号：US10370988B2

公开(公告)日：2019-08-06

申请号：US15214240

申请日：2016-07-19

Applicant: ROLLS-ROYCE plc

Inventor： Steven Hillier

IPC: F01D9/04 ,  F01D25/24 ,  F01D25/00 ,  F01D25/12

Abstract: Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibers held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.

公开(公告)号：US10202860B2

公开(公告)日：2019-02-12

申请号：US15214219

申请日：2016-07-19

Applicant: ROLLS-ROYCE plc

Inventor： Steven Hillier

IPC: B23P15/02 ,  F01D9/06 ,  C04B35/00 ,  F01D9/04 ,  F01D9/02 ,  F01D5/28

Abstract: A method of constructing the nozzle guide passage may include the steps of: providing a tubular pre-form having a plurality of layers of unconsolidated CMC fibers in which the internal walls of the tubular preform provide either working surfaces which define the main gas path walls of the assembled nozzle vane, or extraneous wall portions which do not provide working surfaces of the assembled nozzle guide vane arrangement; cutting the wall portions to provide one or more flaps which remain attached to the pre-form via a connecting portion of wall; and, displacing the flap from a first pre-cut position, to a second consolidation position to provide one or more ancillary features.

公开(公告)号：US20190017400A1

公开(公告)日：2019-01-17

申请号：US16136866

申请日：2018-09-20

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

Inventor： Daniel K. Vetters ,  Peter Broadhead ,  Steven Hillier

IPC: F01D9/06 ,  F01D25/12 ,  F01D9/02 ,  F01D11/08

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.