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1. 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。

2. 发明申请

US20110274559A1 Turbine Airfoil with Body Microcircuits Terminating in Platform 有权
标题翻译：涡轮机翼与机身微电脑终端平台
公开(公告)号：US20110274559A1
公开(公告)日：2011-11-10
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 , B23P15/02
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。

3. 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。

4. 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。

5. 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。

6. 发明授权

US08714927B1 Microcircuit skin core cut back to reduce microcircuit trailing edge stresses 有权
标题翻译：微电路皮芯削减微电路后缘应力
公开(公告)号：US08714927B1
公开(公告)日：2014-05-06
申请号：US13180819
申请日：2011-07-12
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： B22C9/103 , F01D5/187 , F05D2230/211 , F05D2260/941
摘要： A casting system for forming an airfoil portion of a turbine engine component is provided. The casting system includes a main body core for forming at least one internal cavity in the airfoil portion, a microcircuit skin core for forming a cooling microcircuit embedded in a wall of the airfoil portion, and a trailing edge core for forming a cooling passage in a trailing edge of the airfoil portion. The microcircuit skin core has at least one cut-back portion which is sized so as to provide said cooling microcircuit embedded in the wall with a length which allows heat-up of the trailing edge core from a gas path.
摘要翻译：提供一种用于形成涡轮发动机部件的翼型部的铸造系统。铸造系统包括用于在翼型部分中形成至少一个内部空腔的主体芯，用于形成嵌入在翼型部分的壁中的冷却微电路的微电路皮芯，以及用于形成冷却通道的后缘芯机翼部分的后缘。微电路皮肤芯具有至少一个切割部分，其尺寸被设计成使得嵌入在壁中的所述冷却微电路具有允许后缘芯从气体路径加热的长度。

7. 发明申请

US20110123310A1 TURBINE AIRFOIL PLATFORM COOLING CORE 有权
标题翻译：涡轮机空气平台冷却芯
公开(公告)号：US20110123310A1
公开(公告)日：2011-05-26
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： F02C7/18 , F01D5/18 , F01D25/12
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平台和从平台延伸的翼型件。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。

8. 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。

9. 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。

10. 发明申请

US20120168108A1 CASTING CORE ASSEMBLY METHODS 有权
标题翻译：铸造芯组装方法
公开(公告)号：US20120168108A1
公开(公告)日：2012-07-05
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： B22C9/10 , B22D25/02
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。

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