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公开(公告)号：US10935242B2
公开(公告)日：2021-03-02
申请号：US15203914
申请日：2016-07-07
摘要： A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.
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公开(公告)号：US10018067B2
公开(公告)日：2018-07-10
申请号：US14766373
申请日：2014-01-09
发明人： Kevin Samuel Klasing , Richard William Albrecht, Jr. , Brandon Flowers Powell , Mark Willard Marusko , Anthony Venzon , Thomas Ryan Wallace
CPC分类号： F01D11/20 , F01D11/24 , F05D2260/606
摘要： A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.
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公开(公告)号：US20170248030A1
公开(公告)日：2017-08-31
申请号：US15054218
申请日：2016-02-26
CPC分类号： F01D25/12 , F01D11/005 , F01D11/08 , F01D11/24 , F01D25/246 , F02C3/04 , F02C7/18 , F02C7/28 , F05D2220/32 , F05D2230/644 , F05D2240/11 , F05D2250/281 , F05D2260/20
摘要： A shroud for a gas turbine is provided. The shroud can include an outer box having a first wall and a second wall circumferentially spaced apart from the first wall. An inner box is positioned within the outer box. The inner box defines one or more passageways extending therethrough and a first chamber. The inner box and the outer box collectively define a second chamber. The one or more passageways defined by the inner box fluidly couple the first chamber and the second chamber. The first wall of the outer box defines a first boss and first notch, and the second wall of the outer box defines a second boss and notch. A gas turbine is also provided that can include a plurality of such turbine shrouds.
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公开(公告)号：US11920789B2
公开(公告)日：2024-03-05
申请号：US17167165
申请日：2021-02-04
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00014
摘要： A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.
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公开(公告)号：US20210310657A1
公开(公告)日：2021-10-07
申请号：US17167165
申请日：2021-02-04
摘要： A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.
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公开(公告)号：US20170114649A1
公开(公告)日：2017-04-27
申请号：US14921023
申请日：2015-10-23
发明人： Michael J. Verrilli , Mark Eugene Noe , Mark Willard Marusko , Paul Izon , Robert Tyler , Christopher Hasse
CPC分类号： F01D5/282 , C04B35/6269 , C04B37/001 , C04B2235/602 , C04B2235/604 , C04B2237/38 , F01D5/147 , F01D5/30 , F01D11/00 , F05D2220/32 , F05D2230/21 , F05D2230/60 , F05D2240/30 , F05D2250/313 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.
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公开(公告)号：US20240219026A1
公开(公告)日：2024-07-04
申请号：US18432392
申请日：2024-02-05
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00014
摘要： A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.
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公开(公告)号：US20240066590A1
公开(公告)日：2024-02-29
申请号：US18500251
申请日：2023-11-02
发明人： James Herbert Deines , Brian David Przeslawski , Michael John McCarren , Gregory Terrence Garay , Douglas Gerard Konitzer , Mark Willard Marusko , Xi Yang , Brian Patrick Peterson
IPC分类号： B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B28B1/00 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/04 , G03F7/00 , G03F7/20
CPC分类号： B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B22D29/001 , B22D29/002 , B28B1/001 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/041 , G03F7/00 , G03F7/20 , F05D2230/21 , Y02P10/25
摘要： The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
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公开(公告)号：US11813669B2
公开(公告)日：2023-11-14
申请号：US17826742
申请日：2022-05-27
发明人： James Herbert Deines , Brian David Przeslawski , Michael John McCarren , Gregory Terrence Garay , Douglas Gerard Konitzer , Mark Willard Marusko , Xi Yang , Brian Patrick Peterson
IPC分类号： B22D25/02 , B22C9/10 , B22C9/12 , B22C9/02 , B22C9/24 , B22D29/00 , B22C1/22 , F01D9/04 , F01D5/12 , B22C21/14 , B22C13/08 , B29C64/135 , B28B1/00 , B29C64/129 , B22C13/12 , G03F7/00 , B29C64/124 , G03F7/20
CPC分类号： B22D25/02 , B22C1/22 , B22C9/02 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C13/08 , B22C13/12 , B22C21/14 , B22D29/00 , B22D29/001 , B22D29/002 , B28B1/001 , B29C64/124 , B29C64/129 , B29C64/135 , F01D5/12 , F01D9/041 , G03F7/00 , G03F7/20 , F05D2230/21 , Y02P10/25
摘要： Partial integrated core-shell investment casting molds that can be assembled into complete molds are provided herein. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. Core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold are also provided herein.
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公开(公告)号：US20220288673A1
公开(公告)日：2022-09-15
申请号：US17826742
申请日：2022-05-27
发明人： James Herbert Deines , Brian David Przeslawski , Michael John McCarren , Gregory Terrence Garay , Douglas Gerard Konitzer , Mark Willard Marusko , Xi Yang , Brian Patrick Peterson
IPC分类号： B22D25/02 , B22C1/22 , B22C9/10 , B22C9/12 , B22C9/02 , B22C9/24 , B22D29/00 , F01D9/04 , F01D5/12 , B22C21/14 , B22C13/08 , B29C64/135 , B28B1/00 , B29C64/129 , B22C13/12 , G03F7/00 , B29C64/124 , G03F7/20
摘要： The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
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