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公开(公告)号：US11149590B2
公开(公告)日：2021-10-19
申请号：US15992976
申请日：2018-05-30
Applicant: Rolls-Royce Corporation , Rolls-Royce High Temperature Composites, Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Aaron D. Sippel , Ted J. Freeman , Joseph P. Lamusga , Daniel K. Vetters , Sean E. Landwehr , Bruce E. Varney
Abstract: An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.
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公开(公告)号：US11008881B2
公开(公告)日：2021-05-18
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
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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公开(公告)号：US20210062663A1
公开(公告)日：2021-03-04
申请号：US16545791
申请日：2019-08-20
Inventor： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
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公开(公告)号：US10907493B2
公开(公告)日：2021-02-02
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：US20210003024A1
公开(公告)日：2021-01-07
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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Patent Agency Ranking
公开(公告)号：US20200277694A1
公开(公告)日：2020-09-03
申请号：US16804437
申请日：2020-02-28
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites, Inc.
Inventor： Ann Bolcavage , Bradley Wing , Matthew R. Gold
Abstract: In one example, a method for forming an environmental barrier coating (EBC) on a substrate. The method may include depositing an environmental barrier coating (EBC) on a substrate via a thermal spray apparatus to form an as-deposited EBC; heat treating the as-deposited EBC at or above a first temperature for first period of time following the deposition of the as-deposited EBC on the substrate; and cooling the as-deposited EBC to a second temperature following the heat treatment at a controlled rate over a second period of time to form a heat-treated EBC on the substrate. The first temperature, the first period of time, the controlled rate, and the second period of time may be selected to increase a weight percent of crystalline phase in the heat-treated EBC compared to the as-deposited EBC.
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公开(公告)号：US20180371947A1
公开(公告)日：2018-12-27
申请号：US15992976
申请日：2018-05-30
Applicant: Rolls-Royce Corporation , Rolls-Royce High Temperature Composites, Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Aaron D. Sippel , Ted J. Freeman , Joseph P. Lamusga , Daniel K. Vetters , Sean E. Landwehr , Bruce E. Varney
Abstract: An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.
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公开(公告)号：US20170138597A1
公开(公告)日：2017-05-18
申请号：US15217444
申请日：2016-07-22
Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted Joseph Freeman , Bruce E. Varney , Andrew Joseph Lazur
Abstract: An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole therethrough, and a liner tile made of ceramic matrix composite material. A plurality of the liner tile form an annular liner to shield hot combustion gases produced by the gas turbine engine. The liner tile is disposed adjacent the supporting member. A connecting member comprising ceramic material has a base element and a stem. The base element is embedded in the liner tile during construction of the liner tile to form an integrated structure therewith. A distal end of the stem passes through the support hole and is mated with a retaining member to retain the liner tile adjacent the supporting member.
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公开(公告)号：US20160319689A1
公开(公告)日：2016-11-03
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
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。
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公开(公告)号：US20250096623A1
公开(公告)日：2025-03-20
申请号：US18470261
申请日：2023-09-19
Inventor： Benedict N. Hodgson , Robert W. Heeter , Alan W. Smith , Hossein Baninajar
Abstract: A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.
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