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公开(公告)号：US11117838B2
公开(公告)日：2021-09-14
申请号：US15987269
申请日：2018-05-23
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Wayne Steffier , Michael Jacquinto , Stephen Harris , Robert Shinavski , Todd Engel
IPC: C04B35/80 , C04B35/634 , C04B35/638 , C04B35/657 , C04B35/628
Abstract: A method of making a fiber preform for ceramic matrix composite (CMC) fabrication that utilizes a fugitive binder and a machining step is described. The method includes, according to one embodiment, laying up a plurality of plies to form a stack, where each ply comprises an arrangement of fibers. The stack is infiltrated with a polymer at an elevated temperature to form an infiltrated stack that is cooled to form a rigid preform. The rigid fiber preform is machined to have a predetermined shape, such that a machined fiber preform is formed. A composite assembly including the machined fiber preform is formed and then the composite assembly is heated at a sufficient temperature to pyrolyze the polymer. Thus, a porous preform of a predetermined geometry is formed for further processing into a CMC.
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公开(公告)号：US10370997B2
公开(公告)日：2019-08-06
申请号：US14721651
申请日：2015-05-26
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：US10087770B2
公开(公告)日：2018-10-02
申请号：US14721620
申请日：2015-05-26
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：US20170002674A1
公开(公告)日：2017-01-05
申请号：US14789284
申请日：2015-07-01
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites, Inc.
Inventor： Daniel K. Vetters , Todd Engel , Robert J. Shinavski
CPC classification number: F01D25/246 , F05D2240/11 , F05D2250/13 , F05D2250/23 , F05D2300/6033 , Y02T50/672
Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.
Abstract translation: 一种涡轮发动机，包括用于定位在涡轮转子的叶片的径向外侧的涡轮罩。 涡轮机罩包括载体，保持组件和叶片轨道。 刀片轨道由保持组件夹紧，并且保持组件由载体支撑。
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公开(公告)号：US10370998B2
公开(公告)日：2019-08-06
申请号：US14721684
申请日：2015-05-26
Applicant: ROLLS-ROYCE CORPORATION , ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. , ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
Inventor： Daniel Kent Vetters , Todd Engel , Matt Brandt
Abstract: A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the CMC seal segment to the carrier.
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Patent Agency Ranking
公开(公告)号：US10030541B2
公开(公告)日：2018-07-24
申请号：US14789284
申请日：2015-07-01
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites, Inc.
Inventor： Daniel K. Vetters , Todd Engel , Robert J. Shinavski
IPC: F01D25/24
Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.
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公开(公告)号：US20170321567A1
公开(公告)日：2017-11-09
申请号：US15660143
申请日：2017-07-26
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
CPC classification number: F01D11/02 , F01D9/04 , F01D25/246 , F05D2300/6033
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：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：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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