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1. 发明授权

US07097424B2 Micro-circuit platform 有权
标题翻译：微电路平台
公开(公告)号：US07097424B2
公开(公告)日：2006-08-29
申请号：US10771485
申请日：2004-02-03
申请人： Frank Cunha , Keith Santeler , Bret Teller
发明人： Frank Cunha , Keith Santeler , Bret Teller
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2240/81 , F05D2250/185 , F05D2260/22141
摘要： A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro-circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro-circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal convective efficiency, high film coverage, and high cooling effectiveness.
摘要翻译：诸如高压涡轮叶片的燃气涡轮发动机部件在平台内具有翼型部分，平台和微电路，用于冷却邻近翼型部分的压力侧的平台边缘和后缘的平台。微型电路包括在翼型的吸入侧上的第一微型电路和在翼型的压力侧的第二微型电路。平台内的微电路实现了高的热对流效率，高膜覆盖率和高冷却效果。

2. 发明申请

US20050169753A1 Micro-circuit platform 有权
标题翻译：微电路平台
公开(公告)号：US20050169753A1
公开(公告)日：2005-08-04
申请号：US10771485
申请日：2004-02-03
申请人： Frank Cunha , Keith Santeler , Bret Teller
发明人： Frank Cunha , Keith Santeler , Bret Teller
IPC分类号： F01D5/14 , F01D5/18 , F02C7/18 , B63H1/14
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2240/81 , F05D2250/185 , F05D2260/22141
摘要： A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro-circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro-circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal convective efficiency, high film coverage, and high cooling effectiveness.
摘要翻译：诸如高压涡轮叶片的燃气涡轮发动机部件在平台内具有翼型部分，平台和微电路，用于冷却邻近翼型部分的压力侧的平台边缘和后缘的平台。微型电路包括在翼型的吸入侧上的第一微型电路和在翼型的压力侧的第二微型电路。平台内的微电路实现了高的热对流效率，高膜覆盖率和高冷却效果。

3. 发明申请

US20050053459A1 Microcircuit cooling for a turbine airfoil 有权
标题翻译：用于涡轮机翼的微电路冷却
公开(公告)号：US20050053459A1
公开(公告)日：2005-03-10
申请号：US10802260
申请日：2004-03-16
申请人： Frank Cunha , Keith Santeler , Scott Gayman , Eric Couch
发明人： Frank Cunha , Keith Santeler , Scott Gayman , Eric Couch
IPC分类号： F01D5/00 , F01D5/08 , F01D5/18 , F02C7/16 , F02C7/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/25 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.
摘要翻译：涡轮机翼片包括嵌入压力和抽吸侧壁内的多个冷却回路以及第一和第二流动通道。第一流动通道将冷却剂流体供给到仅在压力侧壁内嵌入的冷却回路，而第二流动通道将冷却剂流体供给到仅嵌入在吸力侧壁内的冷却回路。本发明的方法实施例包括将嵌入在第一侧壁内的冷却回路的入口放置成仅与流动通道中的一个流体连通，并且将嵌入在第二侧壁内的冷却回路的入口与至少一个其他流动通道以最小化吸入和压力侧壁的吸收压力的差异，以确保将冷却剂流体摄入相应冷却回路的入口。

4. 发明申请

US20060263221A1 Turbine airfoil platform cooling circuit 有权
标题翻译：涡轮机翼平台冷却回路
公开(公告)号：US20060263221A1
公开(公告)日：2006-11-23
申请号：US11134927
申请日：2005-05-23
申请人： Frank Cunha , Eric Couch , Keith Santeler , Scott Gayman , Eric Hudson , Christopher Joe , Eric Letizia
发明人： Frank Cunha , Eric Couch , Keith Santeler , Scott Gayman , Eric Hudson , Christopher Joe , Eric Letizia
IPC分类号： F01D11/00
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.
摘要翻译：机翼组件包括远离平台延伸的翼型件。通过平台形成一个或多个冷却回路以提供平台的冷却。冷却回路可以包括从平台下方接收冷却空气的向下定向的入口。然后将冷却空气沿大致平行于平台的外表面的方向引导并通过平台的外表面形成的出口。冷却回路可以可选地包括从冷却回路的外壁延伸到内壁的多个基座，以增加冷却回路的刚度和冷却功能。

5. 发明申请

US20050031450A1 Microcircuit airfoil mainbody 有权
标题翻译：微电脑机翼主体
公开(公告)号：US20050031450A1
公开(公告)日：2005-02-10
申请号：US10637352
申请日：2003-08-08
申请人： Frank Cunha , Keith Santeler
发明人： Frank Cunha , Keith Santeler
IPC分类号： F01D5/18 , F02C7/18 , F01D5/08
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A cooling circuit disposed within a first wall portion and a second wall portion of a wall for use in a gas turbine engine is provided. The cooling circuit includes a plurality of inlet apertures disposed in the first wall portion to provide a flow path of cooling air into the cooling circuit, a first exit slot disposed in the second wall portion to provide a cooling air flow path out of the cooling circuit, a plurality of pedestals arranged in rows extending within the between the first wall portion and the second wall portion and a first elongated pedestal disposed radially and extending between the first and second wall portions. The first elongated pedestal is positioned between the pedestals and the first exit slot.
摘要翻译：提供了一种设置在用于燃气涡轮发动机的壁的第一壁部分和第二壁部分内的冷却回路。冷却回路包括设置在第一壁部分中的多个入口孔，以提供冷却空气进入冷却回路的流动路径，第一出口狭槽设置在第二壁部分中，以将冷却空气流动路径提供出冷却回路在所述第一壁部和所述第二壁部之间延伸设置的行的多个基座和径向设置并在所述第一和第二壁部之间延伸的第一细长台座。第一细长基座位于基座和第一出口槽之间。

6. 发明授权

US07575039B2 Refractory metal core coatings 有权
$Refractory metal core coatings$
标题翻译：耐火金属芯涂层
公开(公告)号：US07575039B2
公开(公告)日：2009-08-18
申请号：US10685631
申请日：2003-10-15
申请人： James T. Beals , Joshua Persky , Dilip M. Shah , Venkat Seetharaman , Sudhangshu Bose , Jacob Snyder , Keith Santeler , Carl Verner , Stephen D. Murray , John Marcin , Dinesh Gupta , Daniel A. Bales , Daniel Francis Paulonis , Glenn Cotnoir , John Wiedemer
发明人： James T. Beals , Joshua Persky , Dilip M. Shah , Venkat Seetharaman , Sudhangshu Bose , Jacob Snyder , Keith Santeler , Carl Verner , Stephen D. Murray , John Marcin , Dinesh Gupta , Daniel A. Bales , Daniel Francis Paulonis , Glenn Cotnoir , John Wiedemer
IPC分类号： B22C9/10
CPC分类号： B22C9/10
摘要： A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.
摘要翻译：用于铸造系统的难熔金属芯具有用于在壳体火焰期间提供抗氧化性和防止铸造期间的反应/溶解的涂层。在第一实施例中，涂层包括至少一种氧化物和含硅材料。在第二个实施方案中，涂层包括选自氧化钙，氧化镁，氧化铝，氧化锆，氧化铬，氧化钇，二氧化硅，铪和其混合物的氧化物。在第三实施例中，涂层包括选自氮化硅，赛隆，氮化钛及其混合物的氮化物。在本公开中描述了其它涂层实施例。

7. 发明申请

US20070089850A1 INVESTMENT CASTING CORE METHODS 有权
标题翻译：投资核心方法
公开(公告)号：US20070089850A1
公开(公告)日：2007-04-26
申请号：US10926476
申请日：2004-08-26
申请人： James Beals , Samuel Draper , Jose Lopes , Stephen Murray , Brandon Spangler , Michael Turkington , Bryan Dube , Keith Santeler , Jacob Snyder
发明人： James Beals , Samuel Draper , Jose Lopes , Stephen Murray , Brandon Spangler , Michael Turkington , Bryan Dube , Keith Santeler , Jacob Snyder
IPC分类号： B22C9/04 , B22C9/10
CPC分类号： B22C9/04 , B22C7/02 , B22C9/103 , B22C21/14
摘要： A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.
摘要翻译：牺牲芯用于形成零件的内部空间，并且包括陶瓷芯元件和包括难熔金属元件的第一芯元件。陶瓷芯元件可以模制在第一芯元件上，或者模制成具有允许与第一芯元件组装的组装特征。

8. 发明申请

US20090114797A1 REFRACTORY METAL CORE COATINGS 有权
标题翻译：耐火金属核心涂层
公开(公告)号：US20090114797A1
公开(公告)日：2009-05-07
申请号：US10685631
申请日：2003-10-15
申请人： James T. Beals , Joshua Persky , Dilip M. Shah , Venkat Seetharaman , Sudhangshu Bose , Jacob Snyder , Keith Santeler , Carl Verner , Stephen D. Murray , John J. Marcin , Dinesh Gupta , Daniel A. Bales , Daniel Francis Paulonis , Glenn Cotnoir , John Wiedemer
发明人： James T. Beals , Joshua Persky , Dilip M. Shah , Venkat Seetharaman , Sudhangshu Bose , Jacob Snyder , Keith Santeler , Carl Verner , Stephen D. Murray , John J. Marcin , Dinesh Gupta , Daniel A. Bales , Daniel Francis Paulonis , Glenn Cotnoir , John Wiedemer
IPC分类号： B28B7/28
CPC分类号： B22C9/10
摘要： A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.
摘要翻译：用于铸造系统的难熔金属芯具有用于在壳体火焰期间提供抗氧化性和防止铸造期间的反应/溶解的涂层。在第一实施例中，涂层包括至少一种氧化物和含硅材料。在第二个实施方案中，涂层包括选自氧化钙，氧化镁，氧化铝，氧化锆，氧化铬，氧化钇，二氧化硅，铪和其混合物的氧化物。在第三实施例中，涂层包括选自氮化硅，赛隆，氮化钛及其混合物的氮化物。在本公开中描述了其它涂层实施例。

9. 发明申请

US20070044934A1 Investment casting pattern manufacture 有权
公开(公告)号：US20070044934A1
公开(公告)日：2007-03-01
申请号：US11523960
申请日：2006-09-19
申请人： Keith Santeler
发明人： Keith Santeler
IPC分类号： B22C9/04
CPC分类号： B22C7/02 , B22C9/04 , B22C9/064 , B22C9/103 , B22C21/14
摘要： At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

10. 发明申请

US20070144702A1 COMPOSITE CORE FOR USE IN PRECISION INVESTMENT CASTING 有权
标题翻译：复合核心用于精密投资铸造
公开(公告)号：US20070144702A1
公开(公告)日：2007-06-28
申请号：US11522738
申请日：2006-09-18
申请人： John Wiedemer , Keith Santeler
发明人： John Wiedemer , Keith Santeler
IPC分类号： B22C9/10
CPC分类号： B22C9/103
摘要： A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.
摘要翻译：一种用于熔模铸造工艺的复合芯，所述芯包括陶瓷部分和难熔金属部分，其中所述耐火金属部分被设置为执行多个这种难熔金属元件的功能。特别地，附着到陶瓷元件的后缘的难熔金属元件延伸超过陶瓷元件的尖端的平面，以便替代陶瓷顶端边缘另外延伸的难熔金属元件。难熔金属元件还延伸超过蜡铸造的空间，两者都在尖端和后缘的方向上，使得在铸造过程中促进芯的改进的放置和固定。另一实施例使用延伸到翼型部分和其正交延伸平台部分的单个难熔金属元件。

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