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公开(公告)号：US07513744B2
公开(公告)日：2009-04-07
申请号：US11489155
申请日：2006-07-18
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded in a pressure side wall, a second cooling microcircuit embedded in a suction side wall, and a system for cooling the tip comprising a first tip cooling microcircuit receiving cooling fluid from the first cooling microcircuit and a second tip cooling microcircuit receiving cooling fluid from the second cooling microcircuit.
摘要翻译： 涡轮发动机部件具有具有压力侧，吸力侧，前缘，后缘和末端的翼型部。 该组件还具有嵌入在压力侧壁中的第一冷却微电路，嵌入在吸入侧壁中的第二冷却微电路，以及用于冷却尖端的系统，包括从第一冷却微电路接收冷却流体的第一末端冷却微电路和第二冷却微电路 尖端冷却微电路从第二冷却微电路接收冷却流体。
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公开(公告)号：US20080019839A1
公开(公告)日：2008-01-24
申请号：US11489155
申请日：2006-07-18
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded in a pressure side wall, a second cooling microcircuit embedded in a suction side wall, and a system for cooling the tip comprising a first tip cooling microcircuit receiving cooling fluid from the first cooling microcircuit and a second tip cooling microcircuit receiving cooling fluid from the second cooling microcircuit.
摘要翻译： 涡轮发动机部件具有具有压力侧，吸力侧，前缘，后缘和末端的翼型部。 该组件还具有嵌入在压力侧壁中的第一冷却微电路，嵌入在吸入侧壁中的第二冷却微电路，以及用于冷却尖端的系统，包括从第一冷却微电路接收冷却流体的第一末端冷却微电路和第二冷却微电路 尖端冷却微电路从第二冷却微电路接收冷却流体。
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公开(公告)号：US20080131285A1
公开(公告)日：2008-06-05
申请号：US11606598
申请日：2006-11-30
CPC分类号： B22C9/103 , B22C9/04 , F01D5/147 , F01D5/187 , F05D2230/211 , F05D2300/13 , Y10T29/49337
摘要： A process for forming an airfoil portion of a turbine engine component, such as a turbine blade, is described. The process comprises the steps of placing a ceramic core having a configuration of a passageway to be formed in the airfoil portion within a mold, attaching a refractory metal core element to the ceramic core to stabilize a tip region of the ceramic core, and casting the airfoil portion.
摘要翻译： 描述了用于形成诸如涡轮叶片的涡轮发动机部件的翼型部分的方法。 该方法包括以下步骤：将具有待形成的通道构造的陶瓷芯放置在模具内，将难熔金属芯元件附接到陶瓷芯以稳定陶瓷芯的尖端区域，并将 机翼部分。
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公开(公告)号：US07980819B2
公开(公告)日：2011-07-19
申请号：US11685840
申请日：2007-03-14
申请人： Jason Edward Albert , Atul Kohli , Eric L. Couch
发明人： Jason Edward Albert , Atul Kohli , Eric L. Couch
IPC分类号： F01D5/18
CPC分类号： B22C9/24 , B22C9/04 , B22C9/108 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2260/202 , Y10T29/49341 , Y10T29/49826
摘要： An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.
摘要翻译： 用于涡轮发动机的翼型件包括具有冷却通道的结构，该冷却通道具有相对于结构的外表面布置的大致径向延伸的冷却通道。 冷却通道包括多个冷却槽，从其向外表面延伸并且通过径向延伸的沟槽互连。 沟槽破坏了外表面，外表面提供了沟槽的侧壁。 通过提供具有多个大致轴向延伸的突出部的芯和大致径向延伸的互连突片的韧带来制造翼型件。 该结构围绕芯部形成，以使翼型件具有其外表面。 韧带破坏外表面，以在结构的外表面形成径向延伸的沟槽。
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公开(公告)号：US20120027619A1
公开(公告)日：2012-02-02
申请号：US13159469
申请日：2011-06-14
申请人： Jason Edward Albert , Atul Kohli , Eric L. Couch
发明人： Jason Edward Albert , Atul Kohli , Eric L. Couch
CPC分类号： B22C9/24 , B22C9/04 , B22C9/108 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2260/202 , Y10T29/49341 , Y10T29/49826
摘要： An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.
摘要翻译： 用于涡轮发动机的翼型件包括具有冷却通道的结构，该冷却通道具有相对于结构的外表面布置的大致径向延伸的冷却通道。 冷却通道包括多个冷却槽，从其向外表面延伸并且通过径向延伸的沟槽互连。 沟槽破坏了外表面，外表面提供了沟槽的侧壁。 通过提供具有多个大致轴向延伸的突出部的芯和大致径向延伸的互连突片的韧带来制造翼型件。 该结构围绕芯部形成，以使翼型件具有其外表面。 韧带破坏外表面，以在结构的外表面形成径向延伸的沟槽。
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公开(公告)号：US08695683B2
公开(公告)日：2014-04-15
申请号：US13159469
申请日：2011-06-14
申请人： Jason Edward Albert , Atul Kohli , Eric L. Couch
发明人： Jason Edward Albert , Atul Kohli , Eric L. Couch
IPC分类号： B22C9/10
CPC分类号： B22C9/24 , B22C9/04 , B22C9/108 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2260/202 , Y10T29/49341 , Y10T29/49826
摘要： An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.
摘要翻译： 用于涡轮发动机的翼型件包括具有冷却通道的结构，该冷却通道具有相对于结构的外表面布置的大致径向延伸的冷却通道。 冷却通道包括多个冷却槽，从其向外表面延伸并且通过径向延伸的沟槽互连。 沟槽破坏了外表面，外表面提供了沟槽的侧壁。 通过提供具有多个大致轴向延伸的突出部的芯和大致径向延伸的互连突片的韧带来制造翼型件。 该结构围绕芯部形成，以使翼型件具有其外表面。 韧带破坏外表面，以在结构的外表面形成径向延伸的沟槽。
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公开(公告)号：US20080226462A1
公开(公告)日：2008-09-18
申请号：US11685840
申请日：2007-03-14
申请人： Jason Edward Albert , Atul Kohli , Eric L. Couch
发明人： Jason Edward Albert , Atul Kohli , Eric L. Couch
IPC分类号： F01D5/18
CPC分类号： B22C9/24 , B22C9/04 , B22C9/108 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2260/202 , Y10T29/49341 , Y10T29/49826
摘要： An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.
摘要翻译： 用于涡轮发动机的翼型件包括具有冷却通道的结构，该冷却通道具有相对于结构的外表面布置的大致径向延伸的冷却通道。 冷却通道包括多个冷却槽，从其向外表面延伸并且通过径向延伸的沟槽互连。 沟槽破坏了外表面，外表面提供了沟槽的侧壁。 通过提供具有多个大致轴向延伸的突出部的芯和大致径向延伸的互连突片的韧带来制造翼型件。 该结构围绕芯部形成，以使翼型件具有其外表面。 韧带破坏外表面，以在结构的外表面形成径向延伸的沟槽。
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