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

IPC: F01D5/18 ,  B23P15/02

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。

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

IPC: F01D5/18 ,  B23P15/02

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。

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。

公开(公告)号：US09920635B2

公开(公告)日：2018-03-20

申请号：US14480968

申请日：2014-09-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ramakumar Venkata Naga Bommisetty ,  Dhanvantri Joshi ,  Sridhar Murari ,  Jong Liu ,  Malak Fouad Malak

IPC: F01D5/18 ,  B23P15/02

CPC classification number: F01D5/188 ,  B23P15/02 ,  F01D5/187 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs.

公开(公告)号：US20160069194A1

公开(公告)日：2016-03-10

申请号：US14480968

申请日：2014-09-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ramakumar Venkata Naga Bommisetty ,  Dhanvantri Joshi ,  Sridhar Murari ,  Jong Liu ,  Malak Fouad Malak

IPC: F01D5/18 ,  B23P15/02

CPC classification number: F01D5/188 ,  B23P15/02 ,  F01D5/187 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs.

Abstract translation: 本公开提供了冷却回路的各种实施例，具有冷却回路的涡轮机叶片，以及形成这种涡轮机叶片的方法，其具有可用于燃气涡轮发动机中的凸肋式湍流器结构。 在一个示例性实施例中，公开了一种用于引导流体流动的冷却回路，冷却回路包括冷却回路壁和多个凸起的湍流肋，多个凸起的湍流肋的每个湍流肋与冷却回路间隔开 壁，以允许流体在冷却回路壁和多个湍流肋之间流动。

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

IPC: F01D5/08 ,  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。