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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。

3. 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。

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

US08353329B2 Ceramic core tapered trip strips 有权
标题翻译：陶瓷芯锥形跳闸带
公开(公告)号：US08353329B2
公开(公告)日：2013-01-15
申请号：US12786066
申请日：2010-05-24
申请人： Matthew S. Gleiner , Matthew A. Devore
发明人： Matthew S. Gleiner , Matthew A. Devore
IPC分类号： B22C9/10
CPC分类号： B22C9/10 , B22C7/06 , B22C9/103 , F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2250/292 , F05D2260/22141
摘要： A core for creating an airfoil has a ceramic material that forms a body. The body has an outer dimension, a slot extending through the outer dimension and into the body for receiving an insert, the slot disposed at an angle to the outer dimension, and a trip strip having a first portion disposed in the outer dimension. The first portion is in register with the slot wherein a constant dimension such as minimum thickness is maintained between the trip strip and the slot along a length of the slot and wherein said first portion tapers towards said outer dimension.
摘要翻译：用于制造翼型的芯具有形成主体的陶瓷材料。主体具有外部尺寸，延伸穿过外部尺寸并且进入主体的狭槽，用于接收插入件，与外部尺寸成一定角度设置的狭槽以及具有设置在外部尺寸上的第一部分的脱扣带。所述第一部分与所述槽对准，其中沿着所述槽的长度在所述脱扣带和所述槽之间保持诸如最小厚度的恒定尺寸，并且其中所述第一部分朝着所述外部尺寸逐渐变细。

9. 发明授权

US08974183B2 Ceramic core tapered trip strips 有权
标题翻译：陶瓷芯锥形跳闸带
公开(公告)号：US08974183B2
公开(公告)日：2015-03-10
申请号：US13742749
申请日：2013-01-16
申请人： Matthew S. Gleiner , Matthew A. Devore
发明人： Matthew S. Gleiner , Matthew A. Devore
IPC分类号： B22C9/10 , F01D5/18 , B22C7/06
CPC分类号： B22C9/10 , B22C7/06 , B22C9/103 , F01D5/187 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2250/292 , F05D2260/22141
摘要： A core die for creating an airfoil includes a first section, a second section mating with the first section, and an insert for creating a slot. The first section and the second section define a body having an outer dimension. The insert is disposed at an angle to the outer dimension. A trip strip includes a first portion disposed in the second section. The first portion is in register with the insert and a thickness is maintained between the first portion and the insert along a length of the insert. The first portion tapers towards the outer dimension and the thickness is filled by the ceramic material between the slot and the first portion.
摘要翻译：用于形成翼型的芯模具包括第一部分，与第一部分配合的第二部分和用于产生狭槽的插入件。第一部分和第二部分限定具有外部尺寸的主体。插入件以与外部尺寸成一定角度设置。跳闸带包括设置在第二部分中的第一部分。第一部分与插入件对准，并且沿着插入件的长度在第一部分和插入件之间保持厚度。第一部分朝着外部尺寸渐缩，并且厚度由狭槽和第一部分之间的陶瓷材料填充。

10. 发明申请

US20130236329A1 ROTOR BLADE WITH ONE OR MORE SIDE WALL COOLING CIRCUITS 审中-公开
标题翻译：具有一个或多个侧壁冷却电路的转子叶片
公开(公告)号：US20130236329A1
公开(公告)日：2013-09-12
申请号：US13416822
申请日：2012-03-09
申请人： Matthew A. Devore , Matthew S. Gleiner
发明人： Matthew A. Devore , Matthew S. Gleiner
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/186 , F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/204
摘要： A rotor blade for a gas turbine engine includes an airfoil and a cooling microcircuit. The airfoil includes a first side wall, a second side wall and a tip endwall, where the first side wall and the second side wall extend to and cooperate to form the tip endwall, defining a main cavity between the first side wall and the second side wall. The cooling microcircuit includes a microcircuit cavity, an inlet, a side wall outlet and a tip outlet. The microcircuit cavity is embedded within the first side wall, and the inlet extends from the main cavity to the microcircuit cavity. The side wall outlet extends from the microcircuit cavity to an exterior first side surface of the airfoil. The tip outlet extends from the microcircuit cavity to an exterior tip surface of the airfoil.
摘要翻译：用于燃气涡轮发动机的转子叶片包括翼型件和冷却微型电路。翼型件包括第一侧壁，第二侧壁和末端壁，其中第一侧壁和第二侧壁延伸并协作以形成顶端壁，在第一侧壁和第二侧面之间限定主空腔壁。冷却微电路包括微电路腔，入口，侧壁出口和尖端出口。微电路腔嵌入第一侧壁内，入口从主腔延伸到微电路腔。侧壁出口从微电路腔延伸到翼型的外部第一侧表面。尖端出口从微电路腔延伸到翼型的外部末端表面。

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