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公开(公告)号：US20170226893A1
公开(公告)日：2017-08-10
申请号：US15497757
申请日：2017-04-26
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Edward F. Pietraszkiewicz , Thomas J. Martin , Mark F. Zelesky , Steven B. Gautschi , Matthew A. Devore , Alexander Staroselsky
Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.
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公开(公告)号：US09714580B2
公开(公告)日：2017-07-25
申请号：US14907461
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: 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 provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.
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公开(公告)号：US20170051673A1
公开(公告)日：2017-02-23
申请号：US14827773
申请日：2015-08-17
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
IPC: F02C7/18
CPC classification number: F02C7/18 , F01D5/186 , F05D2220/32 , F05D2260/202
Abstract: A film-cooled component for a gas turbine engine includes a first surface of the component located at a gas path of a gas turbine engine, a second surface of the component defining a component passage, and a cooling airflow passage extending from the second surface to the first surface to convey a cooling airflow from the passage and emit the cooling airflow at the first surface. The cooling airflow passage is curvilinearly diffused in at least two directions relative to a local gas flow direction in the gas path. A method of cooling a component includes flowing a cooling airflow into an internal component passage of the turbine component, conveying the cooling airflow through a cooling airflow passage, diffusing the cooling airflow in at least two directions along the airflow passage, and emitting the cooling airflow at a gas path surface to cool the gas path surface of the component.
Abstract translation: 用于燃气涡轮发动机的薄膜冷却部件包括位于燃气涡轮发动机的气体路径处的部件的第一表面，限定部件通道的部件的第二表面和从第二表面延伸到 所述第一表面用于从所述通道传送冷却气流并且在所述第一表面处发出冷却气流。 冷却气流通道相对于气体路径中的局部气体流动方向在至少两个方向上曲线地扩散。 一种冷却部件的方法包括将冷却气流流入涡轮机部件的内部部件通道，将冷却气流传送通过冷却气流通道，沿着气流通道沿至少两个方向扩散冷却气流，并且发射冷却气流 在气体路径表面处，以冷却部件的气体路径表面。
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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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Patent Agency Ranking
46.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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公开(公告)号：US20160251974A1
公开(公告)日：2016-09-01
申请号：US15028572
申请日：2014-10-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Matthew A. Devore
CPC classification number: F01D9/023 , F01D5/18 , F01D5/188 , F01D9/041 , F01D17/162 , F01D25/12 , F05D2240/121 , F05D2260/201
Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.
Abstract translation: 公开了一种用于燃气涡轮发动机的涡轮叶片组件，包括一个包括压力侧和从前缘向后缘延伸的吸力侧的翼型件。 翼型件可绕垂直于发动机纵向轴线的轴线旋转，并且在翼型件内包括前室，并与冷却空气源连通，前冲击挡板限定前腔室内的预冲击空腔。 预冲击腔被分成前缘腔，压力侧腔和限定在前室的内表面和前冲击挡板的外表面之间的吸力侧空腔。
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公开(公告)号：US20160230664A1
公开(公告)日：2016-08-11
申请号：US15023010
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San Quach , Thomas N. Slavens
CPC classification number: F02C7/18 , F01D5/187 , F01D25/12 , F05D2250/181 , F05D2250/20 , F05D2250/23 , F05D2250/25 , F05D2250/281 , F05D2260/2214 , F05D2260/22141 , Y02T50/676
Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.
Abstract translation: 燃气涡轮发动机部件包括第一侧壁和与第一侧壁间隔开的第二侧壁。 在第一和第二侧壁之间形成至少一个内部冷却通道。 至少一个基座定位在至少一个冷却通道内，并且具有从连接到第一侧壁的第一端延伸到连接到第二侧壁的第二端的主体。 主体包括至少一个突起。
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公开(公告)号：US20160222795A1
公开(公告)日：2016-08-04
申请号：US15022356
申请日：2014-09-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San Quach , Thomas N. Slavens
CPC classification number: F01D5/187 , B22C9/00 , B22C9/10 , B22C9/24 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2230/50 , F05D2240/305 , F05D2240/307 , F05D2260/20 , Y02T50/676
Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.
Abstract translation: 燃气涡轮发动机部件具有从平台延伸到在与平台间隔开的翼型的端部处的尖端的翼型件。 翼型件具有吸力壁和压力壁，至少一个通道从平台向尖端延伸。 一个通风室与至少一个通道通信。 气室从吸力壁向尖端的压力壁流动，以与靠近压力壁的冷却孔相通。 增压室在吸壁和压壁之间具有减小的横截面积，并且在减小的横截面积的下游的横截面面积增加。 还公开了一种模芯。
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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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