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公开(公告)号：US11458530B2
公开(公告)日：2022-10-04
申请号：US16786291
申请日：2020-02-10
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Carl Busta , Lea Dynnette Castle
Abstract: An investment casting process for manufacturing a cast component is provided. The investment casting process includes forming a core, casting the cast component about the core such that a core positioning feature provides a location of an anticipated pilot hole in the cast component, removing the core from the cast component once the casting is completed, locating, forming and sizing a pilot hole to form a resized pilot hole that can receive a sealing plug and installing the sealing plug into the resized pilot hole.
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公开(公告)号：US10443434B2
公开(公告)日：2019-10-15
申请号：US14953745
申请日：2015-11-30
Applicant: United Technologies Corporation
Inventor： Mohammed Ennacer , Russell J. Bergman , Jason B. Moran
Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).
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公开(公告)号：US10378371B2
公开(公告)日：2019-08-13
申请号：US14965501
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman , Thurman Carlo Dabbs
Abstract: A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform. At least two anti-rotation tabs extend axially from the radially outer platform.
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公开(公告)号：US20190153885A1
公开(公告)日：2019-05-23
申请号：US16195316
申请日：2018-11-19
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Russell J. Bergman
Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.
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公开(公告)号：US20170175631A1
公开(公告)日：2017-06-22
申请号：US15450087
申请日：2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
CPC classification number: F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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Patent Agency Ranking
公开(公告)号：US20160369632A1
公开(公告)日：2016-12-22
申请号：US15252874
申请日：2016-08-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Russell J. Bergman
Abstract: A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
Abstract translation: 用于燃气涡轮发动机的部件包括具有非气体通道侧和气体通路侧的平台，从平台的气体路径侧延伸的翼型件和邻近该平台的非气体路径侧定位的盖板 平台。 盖板可以包括将冷却空气的第一部分连通到平台的第一冷却腔的第一多个开口以及可将冷却空气的第二部分连通到第二冷却腔的第二多个开口， 与第一个冷却腔分开。 第一冷却腔和第二冷却腔中的每一个可以包括多个增强特征。
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公开(公告)号：US20160215640A1
公开(公告)日：2016-07-28
申请号：US14605275
申请日：2015-01-26
Applicant: United Technologies Corporation
Inventor： Russell J. Bergman
CPC classification number: F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F16J15/0887
Abstract: The present disclosure includes feather seals for use in gas turbine engines. The feather seals may be used in stationary components such as vanes or blade outer air seals. The feather seals may include stiffening elements, such as round or ovoid dimples, to improve the stiffness of the feather seals.
Abstract translation: 本公开包括用于燃气涡轮发动机的羽毛密封件。 羽毛密封件可用于诸如叶片或叶片外部空气密封件的固定部件中。 羽毛密封件可以包括加强元件，例如圆形或卵形凹坑，以提高羽毛密封件的刚度。
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公开(公告)号：US20160130968A1
公开(公告)日：2016-05-12
申请号：US14937360
申请日：2015-11-10
Applicant: United Technologies Corporation
Inventor： Andrew J. Aggarwala , Russell J. Bergman
CPC classification number: F01D11/04 , F01D9/02 , F01D11/001 , F01D11/005 , F05D2240/127 , F05D2240/57 , F05D2240/80
Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.
Abstract translation: 一个平台包括一个平台体。 平台体具有翼型件支撑表面，与翼型件支撑表面相对的轴向延伸的基座表面和前缘。 前缘包括具有凸起部分的上游延伸凸缘和从凸起部分的下游并且在径向向内的槽部分。 凸起部分和槽部分用于保持流体的涡流。 上游延伸凸缘包括将上游延伸凸缘连接到基座表面的会聚表面。 会聚表面在朝向轴向延伸的基面的方向上会聚，并且相对于基面呈一角度。
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公开(公告)号：US10648353B2
公开(公告)日：2020-05-12
申请号：US14942484
申请日：2015-11-16
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Russell J. Bergman , Mark A. Boeke , Kyle C. Lana , Daniel A. Snyder
Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.
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公开(公告)号：US10458291B2
公开(公告)日：2019-10-29
申请号：US15252874
申请日：2016-08-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Russell J. Bergman
Abstract: A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
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