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公开(公告)号：US20090047136A1
公开(公告)日：2009-02-19
申请号：US11893320
申请日：2007-08-15
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The cooling channel receives cooling air and extends through an interior of the wall portion between the inner diameter end and the outer diameter end. The impingement rib is positioned within the wall portion forward of the cooling channel and between the outer diameter end and the inner diameter end to define a peanut cavity. The impingement rib nozzles extend through the impingement rib for receiving cooling air from the cooling channel. The turbulators are positioned within the peanut cavity to locally influence the flow of the cooling air. The leading edge cooling holes discharge the cooling air from the peanut cavity to an exterior of the wall portion.
摘要翻译： 涡轮机翼片包括壁部分，冷却通道，冲击肋，冲击肋喷嘴，湍流器和前缘冷却孔。 壁部分包括前缘，后缘，外径端和内径端。 冷却通道接收冷却空气并延伸穿过内径端和外径端之间的壁部分的内部。 冲击肋位于冷却通道前方的壁部分之间，并且位于外径端和内径端之间，以限定花生空腔。 冲击肋喷嘴延伸穿过冲击肋，用于从冷却通道接收冷却空气。 扰流器位于花生空腔内以局部地影响冷却空气的流动。 前缘冷却孔将冷却空气从花生腔排出到壁部的外部。
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公开(公告)号：US08083485B2
公开(公告)日：2011-12-27
申请号：US11893320
申请日：2007-08-15
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The cooling channel receives cooling air and extends through an interior of the wall portion between the inner diameter end and the outer diameter end. The impingement rib is positioned within the wall portion forward of the cooling channel and between the outer diameter end and the inner diameter end to define a peanut cavity. The impingement rib nozzles extend through the impingement rib for receiving cooling air from the cooling channel. The turbulators are positioned within the peanut cavity to locally influence the flow of the cooling air. The leading edge cooling holes discharge the cooling air from the peanut cavity to an exterior of the wall portion.
摘要翻译： 涡轮机翼片包括壁部分，冷却通道，冲击肋，冲击肋喷嘴，湍流器和前缘冷却孔。 壁部分包括前缘，后缘，外径端和内径端。 冷却通道接收冷却空气并延伸穿过内径端和外径端之间的壁部分的内部。 冲击肋位于冷却通道前方的壁部分之间，并且位于外径端和内径端之间，以限定花生空腔。 冲击肋喷嘴延伸穿过冲击肋，用于从冷却通道接收冷却空气。 扰流器位于花生空腔内以局部地影响冷却空气的流动。 前缘冷却孔将冷却空气从花生腔排出到壁部的外部。
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公开(公告)号：US20110044795A1
公开(公告)日：2011-02-24
申请号：US12542918
申请日：2009-08-18
IPC分类号： F02C7/18
CPC分类号： F01D5/187 , F01D5/081 , F01D9/06 , F05D2240/81 , F05D2260/201
摘要： A vane for use in a gas turbine engine has a platform connected to an airfoil. There is a cooling passage for supplying cooling air to the platform. A cooling chamber supplies cooling air to a plurality of cooling slots at the platform. The cooling slots have a non-uniform cross section.
摘要翻译： 用于燃气涡轮发动机的叶片具有连接到翼型件的平台。 有一个用于向平台供应冷却空气的冷却通道。 冷却室将冷却空气供应到平台处的多个冷却槽。 冷却槽具有不均匀的横截面。
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公开(公告)号：US08353669B2
公开(公告)日：2013-01-15
申请号：US12542918
申请日：2009-08-18
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F01D5/081 , F01D9/06 , F05D2240/81 , F05D2260/201
摘要： A vane for use in a gas turbine engine has a platform connected to an airfoil. There is a cooling passage for supplying cooling air to the platform. A cooling chamber supplies cooling air to a plurality of cooling slots at the platform. The cooling slots have a non-uniform cross section.
摘要翻译： 用于燃气涡轮发动机的叶片具有连接到翼型件的平台。 有一个用于向平台供应冷却空气的冷却通道。 冷却室将冷却空气供应到平台处的多个冷却槽。 冷却槽具有不均匀的横截面。
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公开(公告)号：US08757974B2
公开(公告)日：2014-06-24
申请号：US11622060
申请日：2007-01-11
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F05D2240/121 , F05D2240/303 , F05D2260/22141
摘要： A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
摘要翻译： 冷却的翼型件包括具有多个开口的冲击肋，所述多个开口将冷却气流从冷却回路流动路径提供给翼型件前缘。 多个开口在与包括鳃孔的外翼面壁相对的冲击肋中偏移。 抵消与包括鳃孔的外翼面相对的开口的多个开口将冷却气流聚焦在湍流器上，以增加冷却气流停留时间，以增加在较高温度翼型区域中的热传递。
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公开(公告)号：US20090074575A1
公开(公告)日：2009-03-19
申请号：US11622060
申请日：2007-01-11
IPC分类号： F01D5/08
CPC分类号： F01D5/186 , F01D5/188 , F05D2240/121 , F05D2240/303 , F05D2260/22141
摘要： A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
摘要翻译： 冷却的翼型件包括具有多个开口的冲击肋，所述多个开口将冷却气流从冷却回路流动路径提供给翼型件前缘。 多个开口在与包括鳃孔的外翼面壁相对的冲击肋中偏移。 抵消与包括鳃孔的外翼面相对的开口的多个开口将冷却气流聚焦在湍流器上，以增加冷却气流停留时间，以增加在较高温度翼型区域中的热传递。
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公开(公告)号：US08393867B2
公开(公告)日：2013-03-12
申请号：US12058940
申请日：2008-03-31
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/201
摘要： An airfoil assembly includes an airfoil with at least one cavity that is in communication with a source of cooling air. A baffle is disposed within that cavity and includes a plurality of openings for directing cooling air against the hot wall. A plurality of dividers extends between the baffle walls and the internal cavity to direct cooling air toward one of a leading edge chamber and a trailing edge chamber.
摘要翻译： 翼型组件包括具有与冷却空气源连通的至少一个空腔的翼型件。 挡板设置在该空腔内，并且包括用于将冷却空气引导到热壁上的多个开口。 多个分隔件在挡板壁和内腔之间延伸，以将冷却空气引向前缘室和后缘室中的一个。
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公开(公告)号：US20090246023A1
公开(公告)日：2009-10-01
申请号：US12058940
申请日：2008-03-31
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/201
摘要： An airfoil assembly includes an airfoil with at least one cavity that is in communication with a source of cooling air. A baffle is disposed within that cavity and includes a plurality of openings for directing cooling air against the hot wall. A plurality of dividers extends between the baffle walls and the internal cavity to direct cooling air toward one of a leading edge chamber and a trailing edge chamber.
摘要翻译： 翼型组件包括具有与冷却空气源连通的至少一个空腔的翼型件。 挡板设置在该空腔内，并且包括用于将冷却空气引导到热壁上的多个开口。 多个分隔件在挡板壁和内腔之间延伸，以将冷却空气引向前缘室和后缘室中的一个。
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公开(公告)号：US06939107B2
公开(公告)日：2005-09-06
申请号：US10717806
申请日：2003-11-19
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A turbine engine component, such as a blade or vane, has a system for cooling a trailing edge portion thereof. The system includes a plurality of rows of pedestals which vary in density along a span of the component. In a preferred embodiment of the present invention, the number of rows of pedestals increases as one moves along the span of the component from an inner diameter region to an outer diameter region.
摘要翻译： 诸如叶片或叶片的涡轮发动机部件具有用于冷却其后缘部分的系统。 该系统包括沿着部件的跨度而沿密度变化的多排基座。 在本发明的优选实施例中，随着沿着部件的跨度从内径区域到外径区域移动，基座的行数增加。
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公开(公告)号：US08197184B2
公开(公告)日：2012-06-12
申请号：US11582594
申请日：2006-10-18
申请人： Young H. Chon
发明人： Young H. Chon
CPC分类号： F01D5/185 , F01D5/288 , F01D9/041 , F05D2230/80 , F05D2230/90 , F05D2240/123 , F05D2240/124 , F05D2240/129 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： A vane cluster has a coated metallic substrate. The cluster includes a platform and a shroud. At least first and second airfoils extend between an outer face of the platform and an inner face of the shroud. Each airfoil has a pressure side and a suction side. The pressure side of the first airfoil faces the suction side of the second airfoil. The cluster includes a cooling passageway system including one or more first feed passageways in the first airfoil and one or more second feed passageways in the second airfoil. At least a first side selected from the pressure side of the first airfoil and the suction side of the second airfoil includes a first region with a local thinning or gap in the coating. Along the first side, the cooling passageway system includes means for locally cooling said first region.
摘要翻译： 叶片簇具有涂覆的金属基底。 集群包括平台和护罩。 至少第一和第二翼型件在平台的外表面和护罩的内表面之间延伸。 每个翼型件具有压力侧和吸力侧。 第一翼型的压力面朝向第二翼型的吸入侧。 集群包括冷却通道系统，其包括在第一翼型中的一个或多个第一进料通道和第二翼型中的一个或多个第二进料通道。 至少从第一翼型的压力侧和第二翼型的吸入侧选择的第一侧包括在涂层中具有局部变薄或间隙的第一区域。 沿着第一侧，冷却通道系统包括用于局部冷却所述第一区域的装置。
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