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1.发明公开Apparatus and methods for providing vane platform cooling 审中-公开Vorrichtung und Verfahren zurKühlungder Plattform einer Leitschaufel
公开(公告)号：EP2019187A2
公开(公告)日：2009-01-28
申请号：EP08252422.4
申请日：2008-07-16
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81
摘要： Apparatus and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform (300) includes: providing a cooling channel (306) on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface (304) and a channel cover (312), the channel cover 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： 提供了用于冷却叶片平台的装置和方法。 在这方面，用于冷却叶片平台（300）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（306），冷却通道由冷却表面（304）和通道盖 （312），所述通道盖与所述冷却表面间隔开并且定位成使得所述冷却表面位于所述叶片的气体流动路径和所述通道盖之间; 并且通过冷却通道引导冷却空气流，使得通过冷却空气的流动从平台的冷却表面提取热量。
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2.发明公开Airfoil cooling arrangement, corresponding casting core mold insert and cooling method 审中-公开Anordnung zurKühlungeines Schaufelprofils，zugehörigeGiesskerneinlage undKühlverfahren
公开(公告)号：EP2374996A2
公开(公告)日：2011-10-12
申请号：EP11160066.4
申请日：2011-03-28
摘要： An example airfoil cooling arrangement includes a airfoil wall (86) having a first face (90) and a second face (94) opposite the first face (90). The airfoil wall (86) establishes a channel (100) that is configured to communicate fluid between an inlet aperture (104) and an outlet aperture (108). The channel (100) includes secondary portion (116) that branch from a primary portion (112). The channel may also comprise a tertiary portion (120) and a quartary portion (124).
摘要翻译： 示例性翼型件冷却装置包括具有第一面（90）和与第一面（90）相对的第二面（94）的翼型件壁（86）。 机翼壁（86）建立通道（100），其被配置成在入口孔（104）和出口孔（108）之间连通流体。 通道（100）包括从主要部分（112）分支的次级部分（116）。 通道还可以包括第三部分（120）和四分部分（124）。
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公开(公告)号：EP2019187B1
公开(公告)日：2018-10-17
申请号：EP08252422.4
申请日：2008-07-16
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81
摘要： Apparatus and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform (300) includes: providing a cooling channel (306) on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface (304) and a channel cover (312), the channel cover 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.
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4.发明公开Full coverage trailing edge microcircuit with alternating converging exits 审中-公开Hutkantenkühlungsmikrokreislaufmit wechselnden konvergierendenAusgängen
公开(公告)号：EP2103781A3
公开(公告)日：2012-11-21
申请号：EP09250645.0
申请日：2009-03-06
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 (100) with a pressure side wall (102), a suction side wall (104), and a trailing edge (108). The turbine engine component further has at least one first cooling circuit core (114) embedded within the pressure side wall (102), with each first cooling circuit core (114) having a first exit (122) for discharging a cooling fluid, at least one second cooling circuit core (116) embedded within the suction side wall (104), with each second cooling circuit core (116) having a second exit (124) for discharging a cooling fluid, and the first and second exits (122, 124) being aligned in a spanwise direction (125) of the airfoil portion (100).
摘要翻译： 涡轮发动机部件具有带有压力侧壁（102），吸力侧壁（104）和后缘（108）的翼型部分（100）。 涡轮发动机部件还具有至少一个嵌入在压力侧壁（102）内的第一冷却回路芯（114），每个第一冷却回路芯（114）具有用于排出冷却流体的第一出口（122），至少 嵌入吸入侧壁（104）内的一个第二冷却回路芯（116），每个第二冷却回路芯（116）具有用于排出冷却流体的第二出口（124），以及第一和第二出口 ）在所述翼型件部（100）的翼展方向（125）上对准。
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6.发明公开Airfoil insert and method for cooling an airfoil 审中-公开Schaufeleinsatz und Verfahren zurKühlungeiner Turbinenschaufel
公开(公告)号：EP2159376A3
公开(公告)日：2012-03-21
申请号：EP09252079.0
申请日：2009-08-27
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： An airfoil insert (10) comprises an insert wall (11), a contact element (14) and a flow director. The insert wall defines an interior (15) extending inside the insert wall from a first end (12) to second end (13), and an exterior (16) extending outside the insert wall from the first end to the second end. The contact element (14) is formed on the exterior of the insert wall (11). The flow director is formed on the insert wall (11) 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.
A method for cooling an airfoil (20) is also disclosed.摘要翻译： 机翼插入件（10）包括插入壁（11），接触元件（14）和导流器。 插入壁限定了从插入壁的第一端部（12）延伸到第二端部（13）内部的内部（15），以及从插入壁的第一端部延伸到第二端部的外部（16）。 接触元件（14）形成在插入壁（11）的外部。 导流器在内壁和外部之间的边界处形成在插入壁（11）上。 流导向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。 还公开了一种用于冷却翼型件（20）的方法。
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公开(公告)号：EP2374996B1
公开(公告)日：2020-07-22
申请号：EP11160066.4
申请日：2011-03-28
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8.发明公开Airfoil cooling arrangement, corresponding casting core mold insert and cooling method 审中-公开安排用于冷却叶片轮廓，相关联Giesskerneinlage和冷却过程
公开(公告)号：EP2374996A3
公开(公告)日：2013-12-18
申请号：EP11160066.4
申请日：2011-03-28
摘要： An example airfoil cooling arrangement includes a airfoil wall (86) having a first face (90) and a second face (94) opposite the first face (90). The airfoil wall (86) establishes a channel (100) that is configured to communicate fluid between an inlet aperture (104) and an outlet aperture (108). The channel (100) includes secondary portion (116) that branch from a primary portion (112). The channel may also comprise a tertiary portion (120) and a quartary portion (124).
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公开(公告)号：EP2019187A3
公开(公告)日：2011-10-19
申请号：EP08252422.4
申请日：2008-07-16
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81
摘要： Apparatus and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform (300) includes: providing a cooling channel (306) on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface (304) and a channel cover (312), the channel cover 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.
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公开(公告)号：EP2159376A2
公开(公告)日：2010-03-03
申请号：EP09252079.0
申请日：2009-08-27
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/202 , Y02T50/67 , Y02T50/676
摘要： An airfoil insert (10) comprises an insert wall (11), a contact element (14) and a flow director. The insert wall defines an interior (15) extending inside the insert wall from a first end (12) to second end (13), and an exterior (16) extending outside the insert wall from the first end to the second end. The contact element (14) is formed on the exterior of the insert wall (11). The flow director is formed on the insert wall (11) 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.
A method for cooling an airfoil (20) is also disclosed.
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