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1.发明授权Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade 有权包括膜冷却系统的涡轮叶片翼型以及用于形成涡轮叶片的改进的薄膜冷却翼型的方法公开(公告)号：US09562437B2
公开(公告)日：2017-02-07
申请号：US13871655
申请日：2013-04-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel C. Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC classification number: F01D5/186 , B23P15/02 , F05D2230/10 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/676 , Y10T29/49341
Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
Abstract translation: 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。
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2.发明申请公开(公告)号：US20200011186A1
公开(公告)日：2020-01-09
申请号：US16555696
申请日：2019-08-29
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeff Howe , Luis Tapia
Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
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3.发明授权Turbine blade airfoils including showerhead film cooling systems, and methods for forming an improved showerhead film cooled airfoil of a turbine blade 有权涡轮叶片翼型件，包括喷头膜冷却系统，以及用于形成涡轮机叶片的改进的喷头薄膜冷却翼型的方法公开(公告)号：US09228440B2
公开(公告)日：2016-01-05
申请号：US13692353
申请日：2012-12-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel Cregg Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC classification number: F01D5/186 , F01D5/187 , F05D2260/202 , Y02T50/676 , Y10T29/49341
Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.
Abstract translation: 提供了涡轮叶片翼型件，喷淋头膜冷却系统以及使用其的用于冷却涡轮叶片翼型件的方法。 翼型件具有在前缘和后缘之间延伸的前缘和后缘，压力侧壁和吸力侧壁，以及用于供应冷却空气的内部空腔。 薄膜冷却孔的喷头连接到内部空腔。 每个膜冷却孔具有连接到内部空腔的入口和在翼型的前缘处的外壁表面上的出口。 多个表面连接器形成在外壁表面中。 多个表面连接器中的每个表面连接器互连至少一个选定的一对薄膜冷却孔的出口。
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4.发明申请公开(公告)号：US20180073368A1
公开(公告)日：2018-03-15
申请号：US15266481
申请日：2016-09-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeff Howe , Luis Tapia
Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
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公开(公告)号：US09777575B2
公开(公告)日：2017-10-03
申请号：US14159043
申请日：2014-01-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Luis Tapia , Steve Halfmann , Stuart Andrew Harman
CPC classification number: F01D5/04 , F01D5/081 , F01D5/18 , F01D5/3007 , F05D2230/60 , Y02T50/676 , Y10T29/49321
Abstract: The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.
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Patent Agency Ranking
6.发明授权公开(公告)号：US10830052B2
公开(公告)日：2020-11-10
申请号：US15266481
申请日：2016-09-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeff Howe , Luis Tapia
Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
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公开(公告)号：US10669862B2
公开(公告)日：2020-06-02
申请号：US16035184
申请日：2018-07-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Luis Tapia , Jason Smoke
IPC: F01D5/18
Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.
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8.发明申请TURBINE BLADE AIRFOILS INCLUDING FILM COOLING SYSTEMS, AND METHODS FOR FORMING AN IMPROVED FILM COOLED AIRFOIL OF A TURBINE BLADE 有权包括薄膜冷却系统的涡轮机叶片，以及用于形成涡轮叶片改进的薄膜冷却气流的方法公开(公告)号：US20140356188A1
公开(公告)日：2014-12-04
申请号：US13871655
申请日：2013-04-26
Applicant: HONEYWELL INTERNATIONAL, INC.
Inventor： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel C. Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC classification number: F01D5/186 , B23P15/02 , F05D2230/10 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/676 , Y10T29/49341
Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
Abstract translation: 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。
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9.发明申请TURBINE BLADE AIRFOILS INCLUDING SHOWERHEAD FILM COOLING SYSTEMS, AND METHODS FOR FORMING AN IMPROVED SHOWERHEAD FILM COOLED AIRFOIL OF A TURBINE BLADE 有权涡轮叶片飞行器，包括淋浴膜冷却系统，以及形成改进的淋浴罩冷却涡轮机叶片的方法公开(公告)号：US20140154096A1
公开(公告)日：2014-06-05
申请号：US13692353
申请日：2012-12-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel Cregg Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/187 , F05D2260/202 , Y02T50/676 , Y10T29/49341
Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.
Abstract translation: 提供了涡轮叶片翼型件，喷淋头膜冷却系统以及使用其的用于冷却涡轮叶片翼型件的方法。 翼型件具有在前缘和后缘之间延伸的前缘和后缘，压力侧壁和吸力侧壁，以及用于供应冷却空气的内部空腔。 薄膜冷却孔的喷头连接到内部空腔。 每个膜冷却孔具有连接到内部空腔的入口和在翼型的前缘处的外壁表面上的出口。 多个表面连接器形成在外壁表面中。 多个表面连接器中的每个表面连接器互连至少一个选定的一对薄膜冷却孔的出口。
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10.发明授权公开(公告)号：US11220918B2
公开(公告)日：2022-01-11
申请号：US17019532
申请日：2020-09-14
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeff Howe , Luis Tapia
Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.
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