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公开(公告)号：US09657584B2
公开(公告)日：2017-05-23
申请号：US15026755
申请日：2014-09-17
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Paul M. Lutjen , Michael J. Bruskotter
Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
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公开(公告)号：US10961862B2
公开(公告)日：2021-03-30
申请号：US16434779
申请日：2019-06-07
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Michael J. Bruskotter , Brian C. McLaughlin , Terence P. Tyler
Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.
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公开(公告)号：US20180298776A1
公开(公告)日：2018-10-18
申请号：US15948596
申请日：2018-04-09
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Paul M. Lutjen , Michael J. Bruskotter
Abstract: An air scal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
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公开(公告)号：US10760443B2
公开(公告)日：2020-09-01
申请号：US15948596
申请日：2018-04-09
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Paul M. Lutjen , Michael J. Bruskotter
Abstract: An air scal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
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公开(公告)号：US09938849B2
公开(公告)日：2018-04-10
申请号：US15026755
申请日：2014-09-17
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Paul M. Lutjen , Michael J. Bruskotter
CPC classification number: F01D11/122 , C23C4/129 , C23C4/134 , C23C4/18 , C23C28/32 , C23C28/3455 , F01D11/02 , F05D2220/32 , F05D2230/312 , F05D2240/11 , F05D2240/55 , F16J15/40
Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
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Patent Agency Ranking
公开(公告)号：US09708922B1
公开(公告)日：2017-07-18
申请号：US15162082
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Mark J. Rogers , Paul M. Lutjen , Terence P. Tyler, Jr. , Michael J. Bruskotter
CPC classification number: F01D11/005 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2250/75 , F05D2300/50 , F16J15/024 , F16J15/0887 , F16J15/44
Abstract: A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.
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公开(公告)号：US10443435B2
公开(公告)日：2019-10-15
申请号：US14969426
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Michael J. Bruskotter , Ross A. Vandenbosch
Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
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公开(公告)号：US20160251976A1
公开(公告)日：2016-09-01
申请号：US15026755
申请日：2014-09-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock , Paul M. Lutjen , Michael J. Bruskotter
CPC classification number: F01D11/122 , C23C4/129 , C23C4/134 , C23C4/18 , C23C28/32 , C23C28/3455 , F01D11/02 , F05D2220/32 , F05D2230/312 , F05D2240/11 , F05D2240/55 , F16J15/40
Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
Abstract translation: 用于燃气涡轮发动机的转子叶片组件的空气密封系统包括基板。 任选的陶瓷中间层可以设置在沉积在基底上的任选粘结涂层上。 在陶瓷中间层（如果存在）或粘合涂层上或衬底上设置耐侵蚀热障涂层（E-TBC）层。 耐磨层设置在抗侵蚀热障涂层（E-TBC）层上。
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公开(公告)号：US20160169039A1
公开(公告)日：2016-06-16
申请号：US14969426
申请日：2015-12-15
Applicant: United Technologies Corporation
Inventor： Richard K. Hayford , Michael J. Bruskotter , Ross A. Vandenbosch
CPC classification number: F01D25/12 , F01D9/04 , F01D11/18 , F01D25/24 , F01D25/246 , F05D2260/221 , F05D2260/941
Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.
Abstract translation: 用于涡轮机的部件包括限定内径部分和外径部分的环形体，以及限定在环形体的表面中的从内径部分向外径向外直径部分延伸的裂缝引导槽， 外径部向径向内侧朝向内径部。 外径部分可以安装在涡轮机的固定结构上。 内径部分可安装在涡轮叶片上。
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公开(公告)号：US20160003082A1
公开(公告)日：2016-01-07
申请号：US14771281
申请日：2014-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul M. Lutjen , Michael J. Bruskotter
CPC classification number: F01D11/12 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2250/711 , F05D2250/712 , F05D2260/202
Abstract: A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.
Abstract translation: 根据本公开的示例性方面的叶片外部空气密封（BOAS）段包括其中具有径向内表面的密封体，所述径向内表面在第一配合面和第二配合面之间周向延伸并且在 前缘面和后缘面，其中径向内表面的径向位置在给定的轴向位置处变化。
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