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1. 发明授权

US09163518B2 Full coverage trailing edge microcircuit with alternating converging exits 有权
标题翻译：全覆盖后缘微电路具有交替的会聚出口
公开(公告)号：US09163518B2
公开(公告)日：2015-10-20
申请号：US12050408
申请日：2008-03-18
申请人： Matthew A. Devore , Eleanor D. Kaufman
发明人： Matthew A. Devore , Eleanor D. Kaufman
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304
摘要： A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.
摘要翻译：涡轮发动机部件具有具有压力侧壁，吸力侧壁和后缘的翼型部分。涡轮发动机部件还具有嵌入在压力侧壁内的至少一个第一冷却回路芯，每个第一冷却回路芯具有用于排出冷却流体的第一出口，嵌入在吸入侧壁内的至少一个第二冷却回路芯，每个第二冷却回路芯具有用于排出冷却流体的第二出口，并且第一和第二出口在翼型部分的翼展方向上对齐。

2. 发明申请

US20130243575A1 COOLING PEDESTAL ARRAY 审中-公开
标题翻译：冷却底盘阵列
公开(公告)号：US20130243575A1
公开(公告)日：2013-09-19
申请号：US13418854
申请日：2012-03-13
申请人： Mark F. Zelesky , Eleanor D. Kaufman
发明人： Mark F. Zelesky , Eleanor D. Kaufman
IPC分类号： F04D31/00
CPC分类号： F01D5/187 , F01D5/141 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/10 , F05D2220/32 , F05D2240/127 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.
摘要翻译：涡轮发动机部件包括由冷却空气流冷却的第一表面。第一表面包括基座阵列和第一排轮廓凸块。基座阵列包括从第一表面延伸的第一和第二排基座。第二排基座在大致平行于第一排基座的方向上延伸。第一排轮廓凸块从第一行基座和第二排基座之间的第一表面延伸并平行于第一排基座延伸。第一排轮廓凸块被对准，使得第一排轮廓凸块的轮廓凸块中的至少一个定位在第一排基座的基座的紧下游的第一排立柱的下游中的至少一个，一排基座。

3. 发明授权

US08016546B2 Systems and methods for providing vane platform cooling 有权
标题翻译：提供叶片平台冷却的系统和方法
公开(公告)号：US08016546B2
公开(公告)日：2011-09-13
申请号：US11782001
申请日：2007-07-24
申请人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
发明人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
IPC分类号： F01D25/12
CPC分类号： F01D5/187 , F05D2240/81
摘要： Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.
摘要翻译：提供了冷却叶片平台的系统和方法。在这方面，用于冷却叶片平台的代表性方法包括：在叶片翼片延伸的平台上提供冷却通道，冷却通道由冷却表面和通道盖限定，通道壁与冷却表面并且定位成使得冷却表面位于叶片的气体流动路径和通道盖之间; 并且通过冷却通道引导冷却空气流，使得通过冷却空气流从平台的冷却表面提取热量。

4. 发明授权

US08449254B2 Branched airfoil core cooling arrangement 有权
标题翻译：分支翼型芯冷却装置
公开(公告)号：US08449254B2
公开(公告)日：2013-05-28
申请号：US12748501
申请日：2010-03-29
申请人： Matthew A. Devore , Eleanor D. Kaufman
发明人： Matthew A. Devore , Eleanor D. Kaufman
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , B22C9/04 , B22C9/10 , F05D2250/185 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2260/2214 , Y02T50/676
摘要： An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.
摘要翻译：示例性翼型件冷却装置包括具有第一面和与第一面相对的第二面的翼型件壁。翼型壁建立了一个通道，该通道被配置成在入口孔和出口孔之间连通流体。该通道包括从主要部分分支的次级部分。示例性翼型件冷却方法包括从翼型芯腔接收流体流并将流体流通过在翼型的壁内的通道。通道具有从主要部分分支的次级部分。

5. 发明申请

US20090028692A1 Systems and Methods for Providing Vane Platform Cooling 有权
标题翻译：提供叶片平台冷却的系统和方法
公开(公告)号：US20090028692A1
公开(公告)日：2009-01-29
申请号：US11782001
申请日：2007-07-24
申请人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
发明人： Raymond Surace , Eleanor D. Kaufman , Andrew D. Milliken , William Abdel-Messeh
IPC分类号： F01D1/02
CPC分类号： F01D5/187 , F05D2240/81
摘要： Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.
摘要翻译：提供了冷却叶片平台的系统和方法。在这方面，用于冷却叶片平台的代表性方法包括：在叶片翼片延伸的平台上提供冷却通道，冷却通道由冷却表面和通道盖限定，通道壁与冷却表面并且定位成使得冷却表面位于叶片的气体流动路径和通道盖之间; 并且通过冷却通道引导冷却空气流，使得通过冷却空气流从平台的冷却表面提取热量。

6. 发明申请

US20110236178A1 BRANCHED AIRFOIL CORE COOLING ARRANGEMENT 有权
标题翻译：分支空气芯芯冷却装置
公开(公告)号：US20110236178A1
公开(公告)日：2011-09-29
申请号：US12748501
申请日：2010-03-29
申请人： Matthew A. Devore , Eleanor D. Kaufman
发明人： Matthew A. Devore , Eleanor D. Kaufman
IPC分类号： F01D25/12 , F01D5/18 , B22D19/00
CPC分类号： F01D5/188 , B22C9/04 , B22C9/10 , F05D2250/185 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2260/2214 , Y02T50/676
摘要： An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.
摘要翻译：示例性翼型件冷却装置包括具有第一面和与第一面相对的第二面的翼型件壁。翼型壁建立了一个通道，该通道被配置成在入口孔和出口孔之间连通流体。通道包括从主要部分分支的次级部分。示例性翼型件冷却方法包括从翼型芯腔接收流体流并将流体流通过在翼型的壁内的通道。通道具有从主要部分分支的次级部分。

7. 发明申请

US20100054915A1 AIRFOIL INSERT 审中-公开
标题翻译：航空插件
公开(公告)号：US20100054915A1
公开(公告)日：2010-03-04
申请号：US12200160
申请日：2008-08-28
申请人： Matthew A. Devore , Eleanor D. Kaufman , Raymond Surace , William Abdel-Messeh
发明人： Matthew A. Devore , Eleanor D. Kaufman , Raymond Surace , William Abdel-Messeh
IPC分类号： F04D29/58 , F01D25/12 , F01D5/18
CPC分类号： F01D5/189 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.
摘要翻译：机翼插入件包括插入壁，接触元件和导流器。插入壁限定从第一端到第二端在插入壁内部延伸的内部，以及从插入壁的第一端延伸到第二端的外部。接触元件形成在插入壁的外部。导流器形成在插入壁上在内部和外部之间的边界处。导流器通过将对流流引导到插入壁的外部来增加沿插入壁的对流流动的传热系数。

8. 发明申请

US20090238695A1 FULL COVERAGE TRAILING EDGE MICROCIRCUIT WITH ALTERNATING CONVERGING EXITS 有权
标题翻译：全面覆盖边缘微型计算机，具有交替的退出
公开(公告)号：US20090238695A1
公开(公告)日：2009-09-24
申请号：US12050408
申请日：2008-03-18
申请人： Matthew A. Devore , Eleanor D. Kaufman
发明人： Matthew A. Devore , Eleanor D. Kaufman
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304
摘要： A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.
摘要翻译：涡轮发动机部件具有具有压力侧壁，吸力侧壁和后缘的翼型部分。涡轮发动机部件还具有嵌入在压力侧壁内的至少一个第一冷却回路芯，每个第一冷却回路芯具有用于排出冷却流体的第一出口，嵌入在吸入侧壁内的至少一个第二冷却回路芯，每个第二冷却回路芯具有用于排出冷却流体的第二出口，并且第一和第二出口在翼型部分的翼展方向上对齐。

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