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公开(公告)号：EP1944470A3
公开(公告)日：2011-09-21
申请号：EP08250095.0
申请日：2008-01-09
CPC分类号： F01D5/188 , B22C9/10 , F01D9/02 , F05D2230/21 , F05D2230/237 , F05D2230/60 , F05D2230/80 , F05D2240/12 , F05D2240/126 , F05D2240/55 , F05D2250/30 , F05D2260/201
摘要： An insertable impingement rib assembly (30) is provided inside a turbine vane (10). The turbine vane (10) has an airfoil portion (12) with a leading edge (14) and a trailing edge (16). The turbine vane (10) has an inner diameter platform (18) and an outer diameter platform (20). A guide channel (32) is located in the airfoil portion (12) of the turbine vane (10). The guide channel (32) has an insertion point, a leading edge guide rail rib (22), a trailing edge guide rail rib (24), and a plurality of apertures (36) therethrough. An impingement rib (34) is insertable into the guide channel (32).
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42.发明公开Recessed standoffs for airfoil baffle 有权Eingedellte Abstandselemente eines EinsatzesfürTurbinenschaufeln
公开(公告)号：EP2233695A1
公开(公告)日：2010-09-29
申请号：EP10250616.9
申请日：2010-03-26
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil (10) comprises an airfoil body (12), a baffle (18) and a plurality of standoffs (34, 36, 56, 74, 76, 78). The airfoil body is shaped to form leading (20) and trailing (26) edges, and pressure (22) and suction (24) sides surrounding an internal cooling channel (30). The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes (28) extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs maintain minimum spacing between the liner body and the airfoil body. The standoffs are recessed into a surface of either the baffle or the airfoil body. In another embodiment, the standoffs are elongated to meter flow between the liner body and the airfoil body.
摘要翻译： 内部冷却的翼型件（10）包括翼型件本体（12），挡板（18）和多个支座（34,36,56,74,76,78）。 机翼本体成形为形成包围内部冷却通道（30）的引导（20）和尾部（26）边缘以及压力（22）和吸力（24）侧。 所述挡板设置在所述内部冷却通道内，并且包括衬套主体，所述衬套主体具有成形为对应于所述内部冷却通道的形状并形成冷却空气供应管道的周边。 挡板包括延伸穿过衬套主体的多个冷却孔（28），以将冷却空气从供应管道引导到内部冷却通道中。 支座保持衬套主体和翼型体之间的最小间距。 挡板凹入挡板或翼型体的表面。 在另一个实施例中，支座被拉长以计量衬套主体和翼型件本体之间的流量。
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43.发明公开A cooled airfoil and an impingement baffle insert therefor 有权GekühltesSchaufelblatt sowiePrallkühleinsatzdafür
公开(公告)号：EP2228517A2
公开(公告)日：2010-09-15
申请号：EP10250478.4
申请日：2010-03-15
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2240/121 , F05D2240/303 , F05D2260/201
摘要： A baffle insert (18) for an internally cooled airfoil (12) comprises a liner, a divoted segment (28,30) and a plurality of cooling holes (32,34). The liner has a continuous perimeter formed to shape a hollow body having a first end and a second end. The divoted segment of the hollow body is positioned between the first end and the second end. The plurality of cooling holes is positioned on the divoted segment to aim cooling air exiting the baffle insert at a common location.
摘要翻译： 用于内部冷却翼型件（12）的挡板（18）包括衬套，分离段（28,30）和多个冷却孔（32,34）。 衬里具有形成为形成具有第一端和第二端的中空本体的连续周边。 中空体的被切断的部分位于第一端和第二端之间。 多个冷却孔位于被分割的段上，以将冷却空气排出离开挡板插入件的公共位置。
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公开(公告)号：EP1944467A3
公开(公告)日：2009-11-18
申请号：EP07254393.7
申请日：2007-11-07
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 (38) includes an impingement rib (54) having a multiple of openings (58) which supply a cooling airflow from a cooling circuit flow path (26) toward an airfoil leading edge (36). The multiple of openings (58) are offset in the impingement rib (54) opposite an outer airfoil wall (40S) which includes gill holes (62). Offsetting the multiple of openings (58) opposite an outer airfoil wall (40S) which includes the gill holes (62) focuses the cooling airflow across turbulators (64) to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.
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公开(公告)号：EP2107214A1
公开(公告)日：2009-10-07
申请号：EP09250728.4
申请日：2009-03-16
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/201
摘要： An airfoil assembly includes an airfoil (16) with at least one cavity (18) that is in communication with a source of cooling air. A baffle (20) is disposed within that cavity (18) and includes a plurality of openings (28) for directing cooling air against the hot wall (32). A plurality of dividers (26) extends between the baffle (20) and the internal cavity (18) to direct cooling air toward one of a leading edge chamber (48) and a trailing edge chamber (50).
摘要翻译： 机翼组件包括具有与冷却空气源连通的至少一个空腔（18）的翼型件（16）。 挡板（20）设置在该空腔（18）内并且包括用于将冷却空气引导到热壁（32）的多个开口（28）。 多个分隔件（26）在挡板（20）和内腔（18）之间延伸，以将冷却空气引向前缘室（48）和后缘室（50）中的一个。
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公开(公告)号：EP2014875A2
公开(公告)日：2009-01-14
申请号：EP08252298.8
申请日：2008-07-04
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F01D9/041 , F01D11/005 , F05D2240/80 , F05D2260/94 , F05D2260/941
摘要： A vane assembly for a gas turbine engine includes: a first mounting platform (106) having a first slot (116); a first airfoil (110) extending from the first mounting platform (106); and a feather seal (104) having opposing faces (120, 122), a first side (126) extending between the faces (120, 122), and a first tab, the first tab (131) extending outwardly beyond the first side (126); the first slot (116) being sized and shaped to receive the feather seal (104) including the first tab (131).
摘要翻译： 一种用于燃气涡轮发动机的叶片组件，包括：具有第一槽（116）的第一安装平台（106） 从所述第一安装平台（106）延伸的第一翼型件（110）; 以及具有相对面（120,122）的羽毛密封件（104），在所述面（120,122）之间延伸的第一侧面（126）和第一凸片，所述第一凸片（131）向外延伸超过所述第一侧面 126）; 第一狭槽（116）的尺寸和形状适于接收包括第一突片（131）的羽毛密封（104）。
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48.发明授权
公开(公告)号：EP2469034B1
公开(公告)日：2019-07-24
申请号：EP11195324.6
申请日：2011-12-22
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公开(公告)号：EP2584143A3
公开(公告)日：2017-05-10
申请号：EP13151206.3
申请日：2009-11-16
发明人： Surace, Raymond , Pigguish, Justin D. , Propheter-Hinckley, Tracy A. , Ramlogan, Amarnath , Xue, Yongxiang D. , Cherolis, Anthony P. , Devore, Matthew A. , Letizia, Eric P.
CPC分类号： F01D5/187 , B22C7/02 , B22C9/043 , B22C9/103 , F01D5/081 , F01D9/041 , F05D2230/211 , F05D2240/122 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , F05D2300/21 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A pattern (140) for casting a component has a pattern material (144) and a casting core combination (142). The pattern material (144) has an airfoil (146). The casting core combination (142) is at least partially embedded in the pattern material (144). The casting core combination (142) comprises a plurality of metallic casting cores (162A-162E). Each metallic casting core has opposite first and second faces (163-164) and a respective portion along the trailing edge of the airfoil (146). At least two of the metallic cores (162A-162E) have sections offset between a pressure side and suction side of the airfoil (146).
摘要翻译： 用于铸造部件的图案（140）具有图案材料（144）和铸芯组合（142）。 图案材料（144）具有翼型件（146）。 铸芯组合（142）至少部分嵌入图案材料（144）中。 铸芯组合（142）包括多个金属铸造型芯（162A-162E）。 每个金属铸芯具有相对的第一和第二面（163-164）以及沿着翼型件（146）的后缘的相应部分。 至少两个金属芯（162A-162E）具有在翼型件（146）的压力侧和吸力侧之间偏移的部分。
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