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公开(公告)号：US20170074112A1
公开(公告)日：2017-03-16
申请号：US15123940
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Graham Ryan Philbrick , Ken Lagueux
CPC classification number: F01D17/105 , F01D11/22 , F01D11/24 , F01D17/145 , F01D21/003 , F01D25/24 , F02C3/13 , F02C7/18 , F02K3/06 , F05D2220/32 , F05D2260/85 , Y02T50/675
Abstract: A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit. A second intake is in fluid communication with the conduit. A valve is configured to selectively direct a fluid from at least one of the first intake and the second intake.
Abstract translation: 燃气涡轮发动机包括导管，其构造成将流体引导到与涡轮部相邻的至少一个歧管。 第一进气口与导管流体连通。 第二进气口与导管流体连通。 阀构造成选择性地引导来自第一进气口和第二进气口中的至少一个的流体。
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公开(公告)号：US09797260B2
公开(公告)日：2017-10-24
申请号：US14694416
申请日：2015-04-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Graham Ryan Philbrick , Ken Lagueux , Bret M. Teller
CPC classification number: F01D5/187 , F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
Abstract: A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.
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公开(公告)号：US10415421B2
公开(公告)日：2019-09-17
申请号：US15425689
申请日：2017-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Arnold , Graham Ryan Philbrick , Patrick D. Couture
Abstract: Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.
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公开(公告)号：US20190078514A1
公开(公告)日：2019-03-14
申请号：US15700328
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joseph F. Englehart , Graham Ryan Philbrick , Henry K. Webster , Richard Seleski , ChaiDee Woods Brown , Michael G. McCaffrey
Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.
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公开(公告)号：US20180223684A1
公开(公告)日：2018-08-09
申请号：US15425689
申请日：2017-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Arnold , Graham Ryan Philbrick , Patrick D. Couture
Abstract: Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.
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Patent Agency Ranking
公开(公告)号：US10914187B2
公开(公告)日：2021-02-09
申请号：US15700288
申请日：2017-09-11
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joseph F. Englehart , Graham Ryan Philbrick , ChaiDee Woods Brown
Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.
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公开(公告)号：US10280783B2
公开(公告)日：2019-05-07
申请号：US15036256
申请日：2014-11-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Graham Ryan Philbrick , Ken Robert Lagueux
Abstract: A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.
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公开(公告)号：US20170226886A1
公开(公告)日：2017-08-10
申请号：US15015667
申请日：2016-02-04
Applicant: United Technologies Corporation
Inventor： Graham Ryan Philbrick , Allison Zywiak
CPC classification number: F01D11/22 , F01D3/04 , F01D5/12 , F01D25/24 , F04D29/052 , F04D29/164 , F04D29/321 , F04D29/526 , F05D2220/32 , F05D2240/52 , F05D2260/30
Abstract: A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.
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公开(公告)号：US20160312638A1
公开(公告)日：2016-10-27
申请号：US15036256
申请日：2014-11-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Graham Ryan Philbrick , Ken Robert Lagueux
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D9/04 , F01D11/001 , F01D11/122 , F05D2220/30 , F05D2240/11 , F05D2240/307 , F05D2300/10 , F05D2300/20
Abstract: A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.
Abstract translation: 涡轮机械密封板包括具有限定具有基板宽度的表面的第一材料的基板。 衬底包括从衬底的末端部分升高并延伸的第一末端延伸部。 第一终端延伸部相对于表面向外延伸直到终点延伸高度。 涡轮机密封板还包括具有覆盖基板的表面并限定涂层宽度的第二材料的涂层。 涂层邻接第一末端延伸部分的一侧。 涂层宽度可以基本上等于末端延伸高度。
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公开(公告)号：US20160222811A1
公开(公告)日：2016-08-04
申请号：US14613692
申请日：2015-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Graham Ryan Philbrick , Patrick D. Couture
CPC classification number: F01D11/08 , B23Q11/005 , B24B19/26 , B24B23/08 , B24B55/10 , F01D5/005 , F01D9/02 , F01D11/10 , F01D25/12 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2230/10 , F05D2230/18 , F05D2240/55
Abstract: A process for machining a turbine engine blade outer air seal in situ, the process comprising replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein the blade outer air seal is assembled in a gas turbine engine case. The process includes coupling a blower to the blade outer air seal. The blade outer air seal comprises at least one flow path. The process includes creating a purge air stream with the blower through the blade outer air seal. The process includes machining the blade outer air seal, wherein particulate is formed from the machining. The process includes preventing the particulate from blocking the at least one flow path of the blade outer air seal.
Abstract translation: 一种用于在现场加工涡轮发动机叶片外部空气密封件的方法，该方法包括用靠近叶片外部空气密封件的切割工具组件替换叶片，其中叶片外部空气密封件组装在燃气涡轮发动机壳体中。 该过程包括将鼓风机连接到叶片外部空气密封件。 叶片外部空气密封件包括至少一个流动路径。 该方法包括通过叶片外部空气密封件与鼓风机产生吹扫空气流。 该方法包括加工叶片外部空气密封件，其中颗粒由机械加工形成。 该方法包括防止颗粒物阻塞叶片外部空气密封件的至少一个流动路径。
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