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公开(公告)号：US10683760B2
公开(公告)日：2020-06-16
申请号：US14713186
申请日：2015-05-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eleanor D. Kaufman , Matthew A. Devore
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.
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公开(公告)号：US20200024970A1
公开(公告)日：2020-01-23
申请号：US16397180
申请日：2019-04-29
Applicant: United Technologies Corporation
Inventor： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
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公开(公告)号：US20190310030A1
公开(公告)日：2019-10-10
申请号：US16280179
申请日：2019-02-20
Applicant: United Technologies Corporation
Inventor： Michael A. Disori , William P. Stillman , Alexander Broulidakis , Dave J. Hyland , Jeremy Styborski , Adam J. Diener , Matthew A. Devore , Dominic J. Mongillo, JR.
Abstract: A featured embodiment of a cast plate heat exchanger assembly includes a cast plate including a plate portion defining a plurality of internal passages. A plurality of fin portions extend from the plate portion. First augmentation structures are disposed on surfaces of the fin portions for conditioning cooling airflow to enhance transfer of thermal energy. A method is also disclosed.
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公开(公告)号：US20190309685A1
公开(公告)日：2019-10-10
申请号：US15946251
申请日：2018-04-05
Applicant: United Technologies Corporation
Inventor： William P. Stillman , Lane Mikal Thornton , Matthew A. Devore , Gavin Hendricks
Abstract: A gas turbine engine includes a compressor section, a combustor section downstream from the compressor section, and a turbine section downstream from the combustor section. The gas turbine engine also includes a water tank with an outlet, and an injector fluidically connected to the outlet of the water tank and to the turbine section. The injector is configured to direct steam from the water tank into the turbine section.
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公开(公告)号：US20190293367A1
公开(公告)日：2019-09-26
申请号：US16276801
申请日：2019-02-15
Applicant: United Technologies Corporation
Inventor： William P. Stillman , Michael A. Disori , Matthew A. Devore , Dave J. Hyland , Adam J. Diener
Abstract: A cast plate heat exchanger includes a first surface including a first surface inlet end and a first group of augmentation features defining a first average density of augmentation features across the first surface. A second surface is in heat transfer communication with the first surface. The second surface includes a second surfaces inlet end and a second group of augmentation features defining a second average density of augmentation features across the second surface. A total augmentation feature density ratio is defined from the first average density of augmentation features to the second average density of augmentation features. A first region is shared by both the first surface and the second surface and covers at least a portion of the first surface inlet end. The first region includes a first region augmentation feature density ratio that is less than the total augmentation feature density ratio.
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Patent Agency Ranking
公开(公告)号：US10329923B2
公开(公告)日：2019-06-25
申请号：US14633677
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Dominic J. Mongillo, Jr. , Matthew A. Devore
Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
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公开(公告)号：US20180128115A1
公开(公告)日：2018-05-10
申请号：US15866134
申请日：2018-01-09
Applicant: United Technologies Corporation
Inventor： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
CPC classification number: F01D5/187 , B22C9/10 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2260/204 , F05D2260/2212
Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
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公开(公告)号：US09376920B2
公开(公告)日：2016-06-28
申请号：US13629705
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： John McBrien , Brandon W. Spangler , Matthew A. Devore
CPC classification number: F01D5/186 , F05D2250/14 , F05D2250/141 , F05D2250/314 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.
Abstract translation: 燃气涡轮发动机部件包括具有外表面的结构。 冷却孔从冷却通道延伸到外表面，以在外表面上形成大致圆形形状的出口区域。 燃气涡轮发动机包括压缩机部和涡轮部。 在压缩机和涡轮机部分之间提供燃烧器。 压缩机和涡轮机部分中的至少一个中的部件具有外表面。 薄膜冷却孔从冷却通道延伸到外表面以提供基本上圆形的出口区域。 一种加工薄膜冷却孔的方法包括提供具有内部冷却通道和外部表面的部件，从外表面到内部冷却通道加工薄膜冷却孔，以在外部表面上提供基本上圆形的出口区域。
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公开(公告)号：US20140196433A1
公开(公告)日：2014-07-17
申请号：US13653633
申请日：2012-10-17
Applicant: United Technologies Corporation
Inventor： Eleanor D. Kaufman , Matthew A. Devore
CPC classification number: F01D5/145 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/81 , F05D2260/2212
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有外表面和在前缘部分和后缘部分之间轴向延伸的内表面的平台。 至少一个增强特征设置在平台的外表面的前缘部分和后缘部分中的至少一个上。
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公开(公告)号：US20200277861A1
公开(公告)日：2020-09-03
申请号：US16739254
申请日：2020-01-10
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Carey Clum , Matthew A. Devore
Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.
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