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公开(公告)号：US20210123354A1
公开(公告)日：2021-04-29
申请号：US16667501
申请日：2019-10-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah J. Zecha , Brian Barainca , Brian Duguay , Uriah C. Noble
IPC: F01D9/04
Abstract: An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.
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公开(公告)号：US10815815B2
公开(公告)日：2020-10-27
申请号：US16031537
申请日：2018-07-10
Applicant: United Technologies Corporation
Inventor： Brian Duguay
Abstract: A method of actuating a Blade Outer Air Seal (BOAS) includes moving a retractor against a portion of a BOAS segment to move the BOAS segment from a first position to a second position that is radially outside the first position. The BOAS segment is seated against a support structure when in the first position and spaced from the support structure when in the second position.
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公开(公告)号：US10301961B2
公开(公告)日：2019-05-28
申请号：US14913785
申请日：2014-07-23
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Brian Duguay
Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.
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公开(公告)号：US09951643B2
公开(公告)日：2018-04-24
申请号：US14781168
申请日：2014-02-06
Applicant: United Technologies Corporation
Inventor： Brian Duguay
CPC classification number: F01D11/22 , F01D11/14 , F01D11/16 , F01D11/20 , F01D25/24 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2270/01
Abstract: An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.
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公开(公告)号：US20160312643A1
公开(公告)日：2016-10-27
申请号：US15102978
申请日：2014-11-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M. Davis , Jose R. Paulino , Brian Duguay
CPC classification number: F01D11/18 , F01D5/02 , F01D5/12 , F01D11/24 , F05D2220/32 , F05D2260/22141 , F05D2300/5021 , F05D2300/50212 , Y02T50/676
Abstract: A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.
Abstract translation: 叶片顶端间隙系统包括第一和第二控制环。 第一控制环具有第一热膨胀系数（CTE）和第一热响应速率。 第二控制环位于第一控制环的径向外部并且可操作地连接到第一控制环，并且具有不同于第一CTE的第二CTE和与第一热响应速率不同的第二热响应速率。 第一和第二控制环的热膨胀和收缩控制叶片顶端间隙系统相对于旋转叶片部件的径向位置。
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Patent Agency Ranking
公开(公告)号：US20160312637A1
公开(公告)日：2016-10-27
申请号：US14697104
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Brian Duguay
CPC classification number: F16J15/3288 , F01D11/005 , F01D25/246 , F05D2240/11 , F05D2240/56 , Y02T50/672
Abstract: As assembly is provided for a gas turbine engine. This assembly includes a component and a brush seal. The component includes a first surface and a second surface. The brush seal includes an annular bundle of bristles which extends longitudinally along an axis to a bundle tip. The bundle of bristles axially contacts the first surface at the bundle tip. The bundle of bristles proximate the bundle tip axially overlaps the second surface, and the bundle of bristles is operable to radially contact the second surface.
Abstract translation: 当为燃气涡轮发动机提供组件时。 该组件包括部件和刷子密封件。 该部件包括第一表面和第二表面。 刷子密封件包括沿轴线纵向延伸至束尖的环形束毛束。 刷毛束在束尖处轴向接触第一表面。 靠近束尖的刷毛束与第二表面轴向重叠，并且刷毛束可操作以径向接触第二表面。
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公开(公告)号：US10832395B2
公开(公告)日：2020-11-10
申请号：US16363545
申请日：2019-03-25
Applicant: United Technologies Corporation
Inventor： Joseph D. Drescher , Kamiko L. Darrow , Brian Duguay , Erik M. Pedersen , Brian Ricciardelli , Danielle N. Balzano
Abstract: A method is provided for inspecting a device comprising a plurality of bristles. During this method, image data provided from an electronic optical sensor is received. The image data is indicative of an image of at least a portion of the bristles. A bristle configuration (e.g., an angle) of at least one of the bristles (e.g., an average bristle) in the image is determined by processing the image data with a computer processor.
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公开(公告)号：US20200025020A1
公开(公告)日：2020-01-23
申请号：US16399254
申请日：2019-04-30
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Brian Duguay
IPC: F01D11/22
Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.
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公开(公告)号：US20190353043A1
公开(公告)日：2019-11-21
申请号：US15982714
申请日：2018-05-17
Applicant: United Technologies Corporation
Inventor： Michael S. Stevens , Christine F. McGinnis , Major D. Jones , Judith F. Brooks , Brian Duguay , Tomasz Pelic
Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.
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10.发明授权公开(公告)号：US10364695B2
公开(公告)日：2019-07-30
申请号：US14780854
申请日：2014-02-06
Applicant: United Technologies Corporation
Inventor： Brian Duguay
Abstract: An active clearance control system for a gas turbine engine includes a ring seal engageable with a multiple of air seal segments.
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