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公开(公告)号：US10012090B2
公开(公告)日：2018-07-03
申请号：US14804865
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder , Andrew D. Burdick
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2220/32 , F05D2240/303 , F05D2250/322 , F05D2260/2212 , Y02T50/676
Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.
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公开(公告)号：US09932835B2
公开(公告)日：2018-04-03
申请号：US14698269
申请日：2015-04-28
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Thomas J. Martin , Brooks E. Snyder
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/187 , F05D2220/30 , F05D2230/21 , F05D2230/22 , F05D2250/25 , F05D2260/20 , F05D2260/201 , F05D2260/2212
Abstract: An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.
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公开(公告)号：US20170051613A1
公开(公告)日：2017-02-23
申请号：US14828063
申请日：2015-08-17
Applicant: United Technologies Corporation
Inventor： Dipanjan Saha , Brooks E. Snyder , Thomas N. Slavens
CPC classification number: F01D5/187 , B22F3/1055 , B22F5/04 , B22F7/08 , B23K26/34 , B23K2101/001 , B33Y10/00 , B33Y80/00 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2240/81 , F05D2260/204 , Y02P10/295 , Y02T50/676
Abstract: An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.
Abstract translation: 形成具有轮廓的端壁的示例性方法包括用至少一个具有来自端壁的开口的冷却通道浇铸端壁，并且以形成在端壁上的杯状轮廓覆盖开口。 示例性的燃气涡轮发动机叶片组件包括具有多个冷却通道的端壁，从端壁径向延伸到尖端的翼型，以及形成在端壁上的杯形轮廓，以在杯形轮廓和径向对置的表面之间提供冷却室 的端壁。
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公开(公告)号：US20170009594A1
公开(公告)日：2017-01-12
申请号：US15113298
申请日：2014-11-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brooks E. Snyder , Thomas N. Slavens
Abstract: A seal for sealing a space defined by first and second components, the seal including at least one first seal and at least one second seal wherein at least a portion of the at least one first seal is disposed in the at least one second seal.
Abstract translation: 用于密封由第一和第二部件限定的空间的密封件，所述密封件包括至少一个第一密封件和至少一个第二密封件，其中所述至少一个第一密封件的至少一部分设置在所述至少一个第二密封件中。
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35.发明申请AN ADDITIVE MANUFACTURED MOLD, A METHOD OF MANUFACTURING THE MOLD, AND A WORKPIECE CASTED FROM THE MOLD 审中-公开一种添加剂制造的模具，一种制造模具的方法以及从该模具制成的工件公开(公告)号：US20160346831A1
公开(公告)日：2016-12-01
申请号：US15112009
申请日：2015-01-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brooks E. Snyder , Thomas N. Slavens , Mark F. Zelesky , James T. Auxier
CPC classification number: B22C9/04 , B22C1/00 , B22C7/02 , B22C9/10 , B22C9/108 , B22C21/14 , B22F3/1055 , B22F5/007 , B22F7/062 , B29C64/153 , B29L2031/757 , B33Y10/00 , B33Y80/00 , Y02P10/292 , Y02P10/295
Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.
Abstract translation: 用于制造铸造工件的模具至少部分地利用添加剂制造工艺制造。 模具可以具有非线性特征的芯，其被附加地制造并与模具的铸模的外壳和/或模具的铸模的外壳接触。 蜡或铸模的外壳也可以相加地制造，并且铸模的外壳可以相加地制造成与芯一体的一块。
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Patent Agency Ranking
公开(公告)号：US20160215644A1
公开(公告)日：2016-07-28
申请号：US14915410
申请日：2014-08-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brooks E. Snyder , Thomas N. Slavens , Mosheshe Camara-Khary Blake
CPC classification number: F01D11/20 , F01D5/12 , F01D5/22 , F01D9/04 , F01D9/041 , F01D11/005 , F01D11/008 , F01D25/24 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/57 , F05D2250/71 , F05D2250/75 , F05D2270/303 , F05D2270/306 , F16J15/0887
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal between the mate face of the first engine component and the mate face of the second engine component. The seal establishes three points of contact with each mate face in at least one condition.
Abstract translation: 本公开的一个示例性实施例涉及包括第一发动机部件和第二发动机部件的燃气涡轮发动机。 第一发动机部件具有与第二发动机部件的配合面相邻的配合面。 发动机还包括在第一发动机部件的配合面与第二发动机部件的配合面之间的密封。 密封件在至少一个条件下与每个配合面建立三个接触点。
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公开(公告)号：US20160177736A1
公开(公告)日：2016-06-23
申请号：US14804424
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder , Andrew D. Burdick
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/306 , F05D2250/314 , F05D2260/201 , Y02T50/676
Abstract: An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.
Abstract translation: 用于燃气涡轮发动机的翼型结构包括一个翼型件，其包括具有至少两个段的吸入侧冷却回路，所述至少两个段由至少一个冲击通道连接。
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公开(公告)号：US10683768B2
公开(公告)日：2020-06-16
申请号：US15113298
申请日：2014-11-14
Applicant: United Technologies Corporation
Inventor： Brooks E. Snyder , Thomas N. Slavens
Abstract: A seal for sealing a space defined by first and second components, the seal including at least one first seal and at least one second seal wherein at least a portion of the at least one first seal is disposed in the at least one second seal.
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公开(公告)号：US10208604B2
公开(公告)日：2019-02-19
申请号：US15140093
申请日：2016-04-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder
Abstract: An internally cooled component of a gas turbine engine is provided. The component may include a cooling passage at least partially defined by a first wall and a second wall with a first pedestal extending from the first wall to the second wall. The first pedestal may have a chevron geometry. A second pedestal may extend from the first wall to the second wall and also have a chevron geometry. A gap may be defined by the first pedestal and the second pedestal with the gap oriented between the first pedestal and the second pedestal.
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公开(公告)号：US10094240B2
公开(公告)日：2018-10-09
申请号：US14620256
申请日：2015-02-12
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder
Abstract: A conduction riser additively manufactured onto thin metal parts, the conduction riser extending in a build direction of the thin metal part and traversing the thin metal part as the conduction riser extends in the build direction. The conduction riser transferring heat from the upper layers of additively manufactured part during manufacturing, preventing thermal deflection of the part.
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