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公开(公告)号：US10989060B2
公开(公告)日：2021-04-27
申请号：US16845820
申请日：2020-04-10
Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc.
Inventor： Daniel K. Vetters , David J. Thomas , Ted Freeman , Joseph Lamusga , Rick Uskert , Douglas D. Dierksmeier , Jun Shi , Todd Engel , Matt Brandt
Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
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公开(公告)号：US10954809B2
公开(公告)日：2021-03-23
申请号：US15989666
申请日：2018-05-25
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Aaron D. Sippel , Bruce E. Varney , Ted J. Freeman , Christopher Barrett
Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.
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公开(公告)号：US10746054B2
公开(公告)日：2020-08-18
申请号：US16249430
申请日：2019-01-16
Applicant: Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Robert J. Shinavski , Zacheriah A. Cole
Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.
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公开(公告)号：US20200095874A1
公开(公告)日：2020-03-26
申请号：US16142850
申请日：2018-09-26
Inventor： Ted J. Freeman , Aaron D. Sippel , Anthony Razzell
IPC: F01D5/30
Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades are coupled with the disk for rotation therewith. The platform system includes a plurality of platforms arranged around the blades and a coverplate that blocks movement of the platforms relative to the disk.
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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
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.
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Patent Agency Ranking
公开(公告)号：US20200025012A1
公开(公告)日：2020-01-23
申请号：US16189648
申请日：2018-11-13
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Daniel Kent Vetters , David J. Thomas , Douglas David Dierksmeier , Jun Shi , Todd Engel
Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
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公开(公告)号：US20190323363A1
公开(公告)日：2019-10-24
申请号：US15959994
申请日：2018-04-23
Applicant: Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Aaron D. Sippel , Andrew Glucklich , Sungbo Shim , Ted J. Freeman
Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.
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公开(公告)号：US20190153899A1
公开(公告)日：2019-05-23
申请号：US16249430
申请日：2019-01-16
Applicant: Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Robert J. Shinavski , Zacheriah A. Cole
CPC classification number: F01D25/246 , F01D11/08 , F05D2230/644 , F05D2240/11 , F05D2240/55 , F05D2300/6033 , Y02T50/672
Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.
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公开(公告)号：US20190048475A1
公开(公告)日：2019-02-14
申请号：US16057984
申请日：2018-08-08
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce PLC
Inventor： Ngunjoh Lawrence Ndamka , Li Li , Ann Bolcavage , Bruce Edward Varney , Sean E. Landwehr
Abstract: A method includes predicting a composition of calcium-magnesium-aluminum-silicate (CMAS) to be encountered by a high temperature mechanical system during use of the high temperature mechanical system. The method further includes selecting a composition of a CMAS-resistant barrier coating layer based at least in part on the predicted composition of CMAS. The CMAS-resistant barrier coating layer includes a base composition and at least one secondary oxide selected based on the predicted composition of CMAS. The at least one secondary oxide includes at least one of an oxide of a divalent element, an oxide of a trivalent element, or an oxide of a tetravalent element. The CMAS-resistant barrier coating layer comprises greater than 0 mol. % and less than about 7 mol. % of the at least one secondary oxide.
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公开(公告)号：US20180328213A1
公开(公告)日：2018-11-15
申请号：US16042809
申请日：2018-07-23
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
CPC classification number: F01D11/08 , F01D9/04 , F01D25/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2240/55 , F05D2300/6033
Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.
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