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公开(公告)号：US11131205B2
公开(公告)日：2021-09-28
申请号：US16677020
申请日：2019-11-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.
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公开(公告)号：US20190003325A1
公开(公告)日：2019-01-03
申请号：US15416144
申请日：2017-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Paul Couey , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
Abstract: A turbine section of a gas turbine engine is provided. The turbine section includes a first turbine with a first inlet and a first outlet; second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least two splitter blades disposed within the inter-turbine duct. The at least two splitter blades include a first splitter blade and a second splitter blade radially interior to the first splitter blade. At least the second splitter blade has a radial position that is greater than 60% of a distance from the shroud to the hub.
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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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公开(公告)号：US20190136702A1
公开(公告)日：2019-05-09
申请号：US15808214
申请日：2017-11-09
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vinayender Kuchana , Balamurugan Srinivasan , Craig Mckeever , Malak Fouad Malak
IPC: F01D9/04
Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.
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公开(公告)号：US10119404B2
公开(公告)日：2018-11-06
申请号：US14515131
申请日：2014-10-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
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Patent Agency Ranking
6.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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公开(公告)号：US20160108740A1
公开(公告)日：2016-04-21
申请号：US14515131
申请日：2014-10-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
CPC classification number: F01D5/187 , F01D5/147 , F01D5/188 , F02C3/04 , F02C7/04 , F02C7/18 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/2214 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
Abstract translation: 用于燃气涡轮发动机的翼型包括具有第一侧壁和在前缘连接的第二侧壁和后缘的主体，第一侧壁具有第一内表面，第二侧壁具有第二内表面。 翼型件还包括设置在主体内部并在第一内表面和第二内表面之间延伸以限定供给通道和前缘通道的内壁。 内壁限定多个冷却孔，以将冷却空气从供应通道引导到前缘通道，使得冷却空气冲击前缘。 所述翼型件还包括形成在所述第一内表面中的第一多个槽，所述第一多个槽在所述前缘通道内沿弦向延伸。
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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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公开(公告)号：US10934856B2
公开(公告)日：2021-03-02
申请号：US16155913
申请日：2018-10-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Balamurugan Srinivasan , Sridharan Reghupathy Narayanan , Karthikeyan Paramanandam , Chandiran Jayamurugan , Malak Fouad Malak
Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
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