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1. 发明授权

US07322795B2 Firm cooling method and hole manufacture 有权
标题翻译：薄膜冷却方法和孔制造
公开(公告)号：US07322795B2
公开(公告)日：2008-01-29
申请号：US11340911
申请日：2006-01-27
申请人： Blake J. Luczak , Eric L. Couch
发明人： Blake J. Luczak , Eric L. Couch
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , B22C9/103 , F02C7/185 , F05D2230/12 , F05D2230/13 , F05D2230/21 , F05D2230/211 , F05D2230/90 , F05D2240/121 , F05D2240/303 , F05D2260/204 , F05D2300/611 , Y02T50/676
摘要： A cooled cast part has an exterior surface. A cooling passageway system extends from at least one inlet port to a plurality of outlet ports. The passageway system includes a first passageway to at least a first of the outlets and surrounding at least one post. The system includes a second passageway to at least a second of the outlets passing through the at least one post.
摘要翻译：冷却的铸造件具有外表面。冷却通道系统从至少一个入口延伸到多个出口。通道系统包括到至少第一出口并围绕至少一个柱的第一通道。该系统包括通过至少一个柱的至少一个第二出口的第二通道。

2. 发明授权

US08393867B2 Chambered airfoil cooling 有权
标题翻译：机翼冷却
公开(公告)号：US08393867B2
公开(公告)日：2013-03-12
申请号：US12058940
申请日：2008-03-31
申请人： Young H. Chon , Tracy A. Propheter-Hinckley , Eric L. Couch
发明人： Young H. Chon , Tracy A. Propheter-Hinckley , Eric L. Couch
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/201
摘要： An airfoil assembly includes an airfoil with at least one cavity that is in communication with a source of cooling air. A baffle is disposed within that cavity and includes a plurality of openings for directing cooling air against the hot wall. A plurality of dividers extends between the baffle walls and the internal cavity to direct cooling air toward one of a leading edge chamber and a trailing edge chamber.
摘要翻译：翼型组件包括具有与冷却空气源连通的至少一个空腔的翼型件。挡板设置在该空腔内，并且包括用于将冷却空气引导到热壁上的多个开口。多个分隔件在挡板壁和内腔之间延伸，以将冷却空气引向前缘室和后缘室中的一个。

3. 发明授权

US07753104B2 Investment casting cores and methods 有权
标题翻译：投资核心和方法
公开(公告)号：US07753104B2
公开(公告)日：2010-07-13
申请号：US11582592
申请日：2006-10-18
申请人： Blake J. Luczak , Eric A. Hudson , James T. Beals , Eric L. Couch
发明人： Blake J. Luczak , Eric A. Hudson , James T. Beals , Eric L. Couch
IPC分类号： B22C9/10 , B22C9/04 , B22C7/02
CPC分类号： B22C9/103 , B22C9/04 , B22C21/14
摘要： A method involves forming a core assembly. The forming includes molding a first ceramic core over a first refractory metal core to form a core subassembly. The subassembly is assembled to a second ceramic core.
摘要翻译：一种方法包括形成芯组件。成型包括在第一耐火金属芯上形成第一陶瓷芯以形成芯子组件。将组件组装到第二陶瓷芯。

4. 发明申请

US20090246023A1 CHAMBERED AIRFOIL COOLING 有权
标题翻译：冷冻空气冷却
公开(公告)号：US20090246023A1
公开(公告)日：2009-10-01
申请号：US12058940
申请日：2008-03-31
申请人： Young H. Chon , Tracy A. Propheter-Hinckley , Eric L. Couch
发明人： Young H. Chon , Tracy A. Propheter-Hinckley , Eric L. Couch
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/201
摘要： An airfoil assembly includes an airfoil with at least one cavity that is in communication with a source of cooling air. A baffle is disposed within that cavity and includes a plurality of openings for directing cooling air against the hot wall. A plurality of dividers extends between the baffle walls and the internal cavity to direct cooling air toward one of a leading edge chamber and a trailing edge chamber.
摘要翻译：翼型组件包括具有与冷却空气源连通的至少一个空腔的翼型件。挡板设置在该空腔内，并且包括用于将冷却空气引导到热壁上的多个开口。多个分隔件在挡板壁和内腔之间延伸，以将冷却空气引向前缘室和后缘室中的一个。

5. 发明申请

US20080226462A1 CAST FEATURES FOR A TURBINE ENGINE AIRFOIL 有权
标题翻译：涡轮发动机气翼的特征
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。

6. 发明申请

US20120027619A1 CAST FEATURES FOR A TURBINE ENGINE AIRFOIL 有权
标题翻译：涡轮发动机气翼的特征
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
IPC分类号： F01D5/00 , B23P15/02 , F01D25/00
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。

7. 发明申请

US20100116452A1 Investment casting cores and methods 有权
公开(公告)号：US20100116452A1
公开(公告)日：2010-05-13
申请号：US11582592
申请日：2006-10-18
申请人： Blake J. Luczak , Eric A. Hudson , James T. Beals , Eric L. Couch
发明人： Blake J. Luczak , Eric A. Hudson , James T. Beals , Eric L. Couch
IPC分类号： B22C9/10 , B22C9/04
CPC分类号： B22C9/103 , B22C9/04 , B22C21/14
摘要： A method involves forming a core assembly. The forming includes molding a first ceramic core over a first refractory metal core to form a core subassembly. The subassembly is assembled to a second ceramic core.

8. 发明授权

US07980819B2 Cast features for a turbine engine airfoil 有权
标题翻译：用于涡轮发动机翼型的铸件特征
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。

9. 发明授权

US08695683B2 Cast features for a turbine engine airfoil 有权
标题翻译：用于涡轮发动机翼型的铸件特征
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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