公开(公告)号：US10316682B2

公开(公告)日：2019-06-11

申请号：US15088852

申请日：2016-04-01

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

Inventor： Daniel K. Vetters ,  Paul A. Davis ,  Simon L. Jones ,  Steven Hillier ,  Peter Broadhead

IPC: F01D11/12 ,  C04B35/83 ,  C04B35/80 ,  F04D29/16 ,  F01D25/00 ,  F01D25/12 ,  F04D29/52

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

公开(公告)号：US10100654B2

公开(公告)日：2018-10-16

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 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12

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：US20160333718A1

公开(公告)日：2016-11-17

申请号：US15088852

申请日：2016-04-01

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

Inventor： Daniel K. Vetters ,  Paul A. Davis ,  Simon L. Jones ,  Steven Hillier ,  Peter Broadhead

IPC: F01D11/12 ,  F04D29/52 ,  F04D29/16 ,  F01D25/00

CPC classification number: F01D11/122 ,  C04B35/803 ,  C04B35/806 ,  C04B35/83 ,  C04B2235/5252 ,  C04B2235/94 ,  F01D11/12 ,  F01D25/005 ,  F01D25/12 ,  F04D29/164 ,  F04D29/526 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/22141 ,  F05D2260/52 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract translation: 用于燃气涡轮发动机的叶片轨道包括多个叶片轨道段。 刀片轨道段围绕中心轴线周向布置以形成刀片轨道。

公开(公告)号：US11274567B2

公开(公告)日：2022-03-15

申请号：US16385725

申请日：2019-04-16

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

Inventor： Daniel K. Vetters ,  Aaron D. Sippel ,  David J. Thomas ,  Andrew J. Eifert ,  Paul A. Davis ,  Simon L. Jones ,  Peter Broadhead ,  Bruce E. Varney ,  Jeffrey A. Walston ,  Steven Hillier

IPC: F01D11/18 ,  F01D11/12 ,  C04B35/83 ,  C04B35/01 ,  C04B35/565 ,  C04B35/80 ,  F01D25/12 ,  F01D25/00 ,  F04D29/16 ,  F04D29/52

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

公开(公告)号：US10563535B2

公开(公告)日：2020-02-18

申请号：US15090134

申请日：2016-04-04

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

Inventor： Daniel K. Vetters ,  Aaron D. Sippel ,  David J. Thomas ,  Andrew J. Eifert ,  Paul A. Davis ,  Simon L. Jones ,  Peter Broadhead ,  Bruce E. Varney ,  Jeffrey A. Walston ,  Steven Hillier

IPC: F01D11/12 ,  F01D25/12 ,  F01D25/00 ,  F04D29/16 ,  F04D29/52 ,  C04B35/80 ,  C04B35/83

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

公开(公告)号：US09759079B2

公开(公告)日：2017-09-12

申请号：US14723909

申请日：2015-05-28

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce High Temperature Composites, Inc. ,  Rolls-Royce plc

Inventor： Aaron D. Sippel ,  Ted J. Freeman ,  David J. Thomas ,  Joseph P. Lamusga ,  Brian J. Shoemaker ,  Steven Hillier

IPC: F01D11/00 ,  F01D25/26 ,  F01D5/22 ,  F01D5/24 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D5/225 ,  F01D5/24 ,  F01D9/04 ,  F01D11/008 ,  F01D25/246 ,  F01D25/26 ,  F01D25/265 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

公开(公告)号：US20140255170A1

公开(公告)日：2014-09-11

申请号：US14196746

申请日：2014-03-04

Applicant: Rolls-Royce PLC

Inventor： Steven Hillier

IPC: F01D11/12 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D11/12 ,  F01D5/282 ,  F01D5/284 ,  F01D9/04 ,  F01D9/041 ,  F01D11/005 ,  F01D11/08 ,  F05D2230/00 ,  F05D2240/11 ,  F05D2240/80 ,  F05D2250/62 ,  F05D2300/6033

Abstract: A component of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (CMC). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine. The sealing portion comprises a recess formed in the CMC and filled with a finer grade ceramic relative to the surrounding CMC, a metal or an intermetallic.

Abstract translation: 燃气涡轮发动机的部件由连续纤维增强陶瓷基复合材料（CMC）形成。 该部件具有在使用中与发动机的相邻部件密封接触的密封部分。 密封部分包括形成在CMC中的凹部，并且相对于周围的CMC，金属或金属间填充有较细等级的陶瓷。

公开(公告)号：US11078802B2

公开(公告)日：2021-08-03

申请号：US16409231

申请日：2019-05-10

Applicant: Rolls-Royce plc

Inventor： Anthony G. Razzell ,  Michael J. Whittle ,  Steven Hillier

IPC: F01D11/00 ,  F16J15/3284

Abstract: A gas turbine engine assembly includes a first component, a second component, and a seal. The first component is spaced apart from the second component to form a gap between the first component and the second component. The seal is configured to block gases from flowing in the gap between the first component and the second component.

公开(公告)号：US10767494B2

公开(公告)日：2020-09-08

申请号：US16379925

申请日：2019-04-10

Applicant: ROLLS-ROYCE plc

Inventor： Steven Hillier

IPC: F01D25/12 ,  F01D5/18 ,  F01D5/28 ,  B28B23/00

Abstract: The disclosure relates to a ceramic matrix composite (CMC) aerofoil. Example embodiments include an aerofoil comprising first and second tubular CMC cores (302, 303) extending along a longitudinal axis of the aerofoil; and an outer CMC layer surrounding the first and second tubular CMC cores (302, 303) and defining an outer shape of the aerofoil having leading and trailing edges, wherein fibres within a wall of the second tubular CMC core extend to the trailing edge of the aerofoil.

公开(公告)号：US20200248573A1

公开(公告)日：2020-08-06

申请号：US16265565

申请日：2019-02-01

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Steven Hillier

IPC: F01D9/04 ,  F01D5/28 ,  F01D5/12 ,  F01D11/00

Abstract: A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.