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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
申请人： ROLLS-ROYCE CORPORATION , ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. , ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
摘要： 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
申请人： ROLLS-ROYCE CORPORATION , ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. , ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
摘要： 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：US12018581B2
公开(公告)日：2024-06-25
申请号：US17857560
申请日：2022-07-05
CPC分类号： F01D5/043 , F01D5/021 , F01D25/12 , F05D2220/32 , F05D2240/24 , F05D2260/221
摘要： A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.
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公开(公告)号：US20210277827A1
公开(公告)日：2021-09-09
申请号：US16813491
申请日：2020-03-09
发明人： Douglas David Dierksmeier , Douglas Boyd , Douglas J. Snyder , Graham Burkholder , William Barry Bryan
IPC分类号： F02C7/10
摘要： A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.
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公开(公告)号：US11028715B2
公开(公告)日：2021-06-08
申请号：US16149499
申请日：2018-10-02
摘要： An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.
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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
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
摘要： 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：US10989062B2
公开(公告)日：2021-04-27
申请号：US16388152
申请日：2019-04-18
摘要： An assembly is disclosed for adjusting the radial position of a blade track relative to a blade of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a blade track carrier, a blade track support assembly, an actuator, and a blade track. The blade track carrier comprises a pair of radially extending flanges each defining at least one bore in radial and axial alignment with each other forming a pair of bores. The blade track support assembly comprises a portion extending through each bore in a pair of bores, and one or more cam-shaped portions rotatable about an axis of rotation. The blade track has an arcuate flange and a support flange, the support flange being carried by the cam-shaped portion of the blade track support assembly such that rotation of the cam-shaped portion effects radial movement of the blade track.
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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
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc.
摘要： 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：US10704408B2
公开(公告)日：2020-07-07
申请号：US15970495
申请日：2018-05-03
摘要： A blade track system includes an outer ring coupled with a blade track, and an inner ring positioned concentrically between the outer ring and the blade track. The outer ring designed to radially expand, at a first predetermined rate, in response to acceleration of a gas turbine engine. The segments of the blade track radially outwardly expanded away from a hub of the gas turbine engine by the radial expansion of the outer ring. The inner ring designed to radially contract inwardly toward the hub of the gas turbine engine at a second predetermined rate in response to deceleration of the gas turbine. The first predetermined rate being greater than the second predetermined rate, and radial contraction of the outer ring and the segments of the blade track constrained to the predetermined rate of contraction of the inner ring.
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公开(公告)号：US20190338663A1
公开(公告)日：2019-11-07
申请号：US15970495
申请日：2018-05-03
摘要： A blade track system includes an outer ring coupled with a blade track, and an inner ring positioned concentrically between the outer ring and the blade track. The outer ring designed to radially expand, at a first predetermined rate, in response to acceleration of a gas turbine engine. The segments of the blade track radially outwardly expanded away from a hub of the gas turbine engine by the radial expansion of the outer ring. The inner ring designed to radially contract inwardly toward the hub of the gas turbine engine at a second predetermined rate in response to deceleration of the gas turbine. The first predetermined rate being greater than the second predetermined rate, and radial contraction of the outer ring and the segments of the blade track constrained to the predetermined rate of contraction of the inner ring.
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