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1. 发明授权

US08251123B2 Casting core assembly methods 有权
标题翻译：铸芯组装方法
公开(公告)号：US08251123B2
公开(公告)日：2012-08-28
申请号：US12981650
申请日：2010-12-30
申请人： John R. Farris , Tracy A. Propheter-Hinckley , Douglas C. Jenne , Matthew S. Gleiner , Peter H. Thomas
发明人： John R. Farris , Tracy A. Propheter-Hinckley , Douglas C. Jenne , Matthew S. Gleiner , Peter H. Thomas
IPC分类号： B22C9/04 , B22C9/10
CPC分类号： B22C9/103 , B22C9/108
摘要： A casting core assembly includes a metallic core and a ceramic core. The process for forming the casting core assembly includes inserting a ceramic plug of a metallic core and ceramic plug core subassembly into a compartment of the ceramic core. The ceramic plug is secured to the ceramic core.
摘要翻译：铸造芯组件包括金属芯和陶瓷芯。用于形成铸造芯组件的方法包括将金属芯和陶瓷插塞芯子组件的陶瓷塞插入到陶瓷芯的隔室中。陶瓷插头固定在陶瓷芯上。

2. 发明申请

US20110243717A1 DEAD ENDED BULBED RIB GEOMETRY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机的封闭式RIB几何
公开(公告)号：US20110243717A1
公开(公告)日：2011-10-06
申请号：US12754704
申请日：2010-04-06
申请人： Matthew S. Gleiner , Douglas C. Jenne
发明人： Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F02C7/12
CPC分类号： F01D5/187 , F05D2250/185
摘要： A component within a gas turbine engine includes a dead ended rib which at least partially defines an internal cooling circuit flow path, the dead ended rib defines a bulbed rib profile.
摘要翻译：燃气涡轮发动机中的部件包括至少部分地限定内部冷却回路流动路径的死端肋，死端肋限定凸肋状轮廓。

3. 发明申请

US20110123311A1 SERPENTINE CORED AIRFOIL WITH BODY MICROCIRCUITS 有权
标题翻译： SERPENTINE CORED AIRFOIL与身体微型摄影机
公开(公告)号：US20110123311A1
公开(公告)日：2011-05-26
申请号：US12623703
申请日：2009-11-23
申请人： Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
发明人： Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F02C7/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/204
摘要： A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall.
摘要翻译：燃气涡轮发动机部件具有从前缘延伸到后缘以及吸力侧并具有压力侧的翼型件。有从翼型的根部向翼型的尖端延伸的冷却通道。冷却通道包括从根部向尖端延伸并且与前缘相邻的直通道。蛇形通道具有至少三个连接的路径，并且与直通道朝向后缘间隔开。在压力壁和三条蛇形路径中的每一条和直线路径之间设置冷却回路。在吸入壁和直通道之间设有冷却回路。在蛇形通道的至少三条路径中的至少一个下游侧和吸入壁之间不存在冷却。

4. 发明授权

US08794911B2 Anti-rotation slot for turbine vane 有权
标题翻译：用于涡轮叶片的防旋转槽
公开(公告)号：US08794911B2
公开(公告)日：2014-08-05
申请号：US12749971
申请日：2010-03-30
申请人： Richard M. Murphy , Matthew S. Gleiner
发明人： Richard M. Murphy , Matthew S. Gleiner
IPC分类号： F01D9/02
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/642 , F05D2240/80 , F05D2250/62 , F05D2260/31 , F05D2260/941 , Y10T29/49336
摘要： A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation.
摘要翻译：用于燃气涡轮发动机的固定叶片部分包括防旋转槽，其接收销以保持期望位置，同时提供在操作期间遇到的运动。示例性防旋转槽包括内表面上的复合半径，以减少操作期间遇到的应力。

5. 发明授权

US08562286B2 Dead ended bulbed rib geometry for a gas turbine engine 有权
标题翻译：燃气涡轮发动机的死端凸肋几何形状
公开(公告)号：US08562286B2
公开(公告)日：2013-10-22
申请号：US12754704
申请日：2010-04-06
申请人： Matthew S. Gleiner , Douglas C. Jenne
发明人： Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185
摘要： A component within a gas turbine engine includes a dead ended rib which at least partially defines an internal cooling circuit flow path, the dead ended rib defines a bulbed rib profile.
摘要翻译：燃气涡轮发动机中的部件包括至少部分地限定内部冷却回路流动路径的死端肋，死端肋限定凸肋状轮廓。

6. 发明授权

US08511994B2 Serpentine cored airfoil with body microcircuits 有权
标题翻译：蛇形核心翼型机身微电路
公开(公告)号：US08511994B2
公开(公告)日：2013-08-20
申请号：US12623703
申请日：2009-11-23
申请人： Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
发明人： Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/204
摘要： A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall.
摘要翻译：燃气涡轮发动机部件具有从前缘延伸到后缘以及吸力侧并具有压力侧的翼型件。有从翼型的根部向翼型的尖端延伸的冷却通道。冷却通道包括从根部向尖端延伸并且与前缘相邻的直通道。蛇形通道具有至少三个连接的路径，并且与直通道朝向后缘间隔开。在压力壁和三条蛇形路径中的每一条和直线路径之间设置冷却回路。在吸入壁和直通道之间设有冷却回路。在蛇形通道的至少三条路径中的至少一个下游侧和吸入壁之间不存在冷却。

7. 发明申请

US20130205792A1 COOLING HOLE WITH ASYMMETRIC DIFFUSER 有权
标题翻译：冷却孔与不对称扩散器
公开(公告)号：US20130205792A1
公开(公告)日：2013-08-15
申请号：US13544136
申请日：2012-07-09
申请人： Matthew S. Gleiner , Atul Kohli , Mark F. Zelesky
发明人： Matthew S. Gleiner , Atul Kohli , Mark F. Zelesky
IPC分类号： F02C7/18 , F01D25/12 , F04D29/58 , F01D5/08
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/324 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676 , Y10T29/49323
摘要： A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.
摘要翻译：燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。漫射部分包括从计量部分纵向分散的第一凸角和邻近第一凸角的第二凸角并且从计量部分纵向和横向发散。

8. 发明授权

US08356978B2 Turbine airfoil platform cooling core 有权
标题翻译：涡轮机翼平台冷却芯
公开(公告)号：US08356978B2
公开(公告)日：2013-01-22
申请号：US12623666
申请日：2009-11-23
申请人： Jeffrey S. Beattie , Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
发明人： Jeffrey S. Beattie , Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F01D5/00
CPC分类号： F01D5/18 , B22C9/10 , F01D9/02 , F05D2240/81 , F05D2260/20
摘要： A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform.
摘要翻译：燃气涡轮发动机部件具有从平台延伸的平台和翼型件。该平台具有压力侧和吸力侧。在平台内形成冷却通道，并沿平台的压力侧延伸。空气通过平台的吸入侧的出气口离开通道。

9. 发明授权

US09121290B2 Turbine airfoil with body microcircuits terminating in platform 有权
标题翻译：涡轮机翼与机体微电路终止于平台
公开(公告)号：US09121290B2
公开(公告)日：2015-09-01
申请号：US12774771
申请日：2010-05-06
申请人： Douglas C. Jenne , Matthew S. Gleiner , Matthew A. Devore
发明人： Douglas C. Jenne , Matthew S. Gleiner , Matthew A. Devore
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/204 , Y10T29/49341
摘要： A turbine engine component includes a platform and one or more microcircuit cooling passages embedded within one or more walls of an airfoil portion of the component. Each microcircuit cooling passage terminates within the thickness of the platform so as to provide cooling to the initial 10% span of the airfoil portion. Each microcircuit cooling passage has an inlet for receiving cooling fluid, which inlet is also embedded within the platform.
摘要翻译：涡轮发动机部件包括一个平台和一个或多个微型电路冷却通道，其嵌入该部件的翼型部分的一个或多个壁内。每个微电路冷却通道终止在平台的厚度内，以便为翼型部分的初始10％跨度提供冷却。每个微电路冷却通道具有用于接收冷却流体的入口，该入口也嵌入在平台内。

10. 发明授权

US08763402B2 Multi-lobed cooling hole and method of manufacture 有权
标题翻译：多叶冷却孔及制造方法
公开(公告)号：US08763402B2
公开(公告)日：2014-07-01
申请号：US13544090
申请日：2012-07-09
申请人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
发明人： JinQuan Xu , Mark F. Zelesky , Atul Kohli , Matthew S. Gleiner
IPC分类号： F02C1/00
CPC分类号： F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.
摘要翻译：燃气涡轮发动机部件包括冷却孔。冷却孔包括入口，出口，计量部分和扩散部分。扩散部分从计量部分延伸到出口并且包括从计量部分纵向和横向发散的第一凸角，邻近第一凸角并从计量部分纵向和横向发散的第二凸角，以及过渡区域，其具有在第一和第二凸角之间延伸，并且邻近出口延伸。

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