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31.发明申请公开(公告)号：US20130025812A1
公开(公告)日：2013-01-31
申请号：US13193956
申请日：2011-07-29
CPC分类号： F01D5/187 , B22C9/103 , F05D2230/10 , F05D2230/20 , F05D2230/50
摘要： A method of molding a platform opening includes the steps of providing a main body core and a platform core, with the main body core having a portion that forms a portion of the platform. The platform core has at least one side portion that will form a side opening. Molten metal is directed around the cores within a mold and solidifies. The cores are removed, leaving cavities where the cores were within the molten metal, and includes an opening in a side face formed by the side portion of the platform body core. Lost core components are also disclosed and claimed.
摘要翻译： 模制平台开口的方法包括提供主体芯和平台芯的步骤，主体芯具有形成平台的一部分的部分。 平台芯具有形成侧开口的至少一个侧部。 熔融金属被引导在模具中的芯周围并固化。 将芯除去，留下芯在熔融金属内的空腔，并且包括由平台本体芯的侧部形成的侧面中的开口。 丢失的核心组件也被披露并要求保护。
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公开(公告)号：US20120163975A1
公开(公告)日：2012-06-28
申请号：US12975416
申请日：2010-12-22
CPC分类号： F01D9/041 , F01D11/24 , F05D2230/21 , F05D2230/232 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： A turbine engine component has an airfoil portion, which airfoil portion is bounded by a platform at one end. The platform has an as-cast open cavity bordered by at least one as-cast landing. A plate is welded to the at least one as-cast landing to cover and close the as-cast open cavity. A process for forming the turbine engine component is described.
摘要翻译： 涡轮发动机部件具有翼型部分，翼型部分在一端由平台限定。 该平台具有由至少一个演员着陆界定的演习开放空腔。 板被焊接到至少一个铸造着陆部以覆盖和关闭铸态开放腔。 描述了用于形成涡轮发动机部件的过程。
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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：US07922444B2
公开(公告)日：2011-04-12
申请号：US11655546
申请日：2007-01-19
IPC分类号： F01D9/04
CPC分类号： F01D11/005 , F05D2230/21 , F05D2240/11 , F05D2240/55 , F05D2250/192 , F05D2250/292 , Y02T50/671 , Y10T29/49297
摘要： A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from a leading edge to a trailing edge of the shroud rail, and a slot wall extending generally perpendicularly from the slot base. The chamfer rail pocket comprises a pocket wall extending along the slot wall, and a chamfer wall extending from the pocket wall at an angle oblique to the slot base.
摘要翻译： 用于将羽毛密封件保持在燃气涡轮发动机的叶片护罩中的护罩导轨包括用于接收羽毛密封件的槽和用于减轻护罩导轨的倒角轨道槽。 狭槽横过叶片护罩并且包括从护罩导轨的前缘延伸到后缘的槽基座以及从槽基座大致垂直延伸的槽壁。 倒角轨道槽包括沿着槽壁延伸的袋壁和从凹槽壁以与槽基部倾斜的角度延伸的倒角壁。
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公开(公告)号：US20100129194A1
公开(公告)日：2010-05-27
申请号：US12275777
申请日：2008-11-21
申请人： Tracy A. Propheter-Hinckley , Justin D. Piggush , Yongxiang D. Xue , Amarnath Ramlogan , Anthony P. Cherolis , Matthew A. Devore , Eric P. Letizia
发明人： Tracy A. Propheter-Hinckley , Justin D. Piggush , Yongxiang D. Xue , Amarnath Ramlogan , Anthony P. Cherolis , Matthew A. Devore , Eric P. Letizia
CPC分类号： F01D5/187 , B22C7/00 , B22C7/02 , B22C9/043 , B22C9/10 , B22C9/103 , B22C9/24 , B22D25/06 , F01D5/147 , F01D5/18 , F01D5/3007 , F05D2230/21 , F05D2300/13 , F05D2300/611 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.
摘要翻译： 该图案具有图案材料和铸造芯组合。 图案材料具有翼型。 铸造芯组合至少部分地嵌入图案材料中。 铸造芯组合包括金属铸造芯和至少一个另外的铸芯。 金属铸造芯具有相对的第一和第二面。 金属芯和至少一个额外的铸芯将翼展方向延伸到图案材料的翼型中。 在图案材料的翼型外部的图案材料的至少一部分中，金属铸造芯横向于翼展方向弯曲，以便至少部分地围绕至少一个附加铸芯的相邻部分。
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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：US20080099178A1
公开(公告)日：2008-05-01
申请号：US11589581
申请日：2006-10-30
IPC分类号： B22D29/00
摘要： A molding technique is utilized to form the cooling channels in an airfoil for a gas turbine engine. The cooling channels are formed by lost core mold plugs, which are leached away after metal has been molded around them. At least one of the mold plugs is provided with a cone which will extend into the airfoil. The cone forms an opening in a wall of the airfoil, and the size of this opening is indicative of the thickness of the wall. By comparing the size to expected sizes, a determination can be made of whether the wall is of an acceptable thickness at locations where it is difficult to otherwise measure the wall.
摘要翻译： 利用模制技术在燃气涡轮发动机的翼型中形成冷却通道。 冷却通道由失去的芯模插头形成，金属模制在其周围时被淋出。 至少一个模具塞具有将延伸到翼型中的锥体。 锥体在翼型件的壁中形成开口，并且该开口的尺寸表示壁的厚度。 通过将尺寸与预期尺寸进行比较，可以确定在难以另外测量壁的位置处壁是否具有可接受的厚度。
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公开(公告)号：US09273566B2
公开(公告)日：2016-03-01
申请号：US13531001
申请日：2012-06-22
CPC分类号： F01D17/162 , F05D2260/202
摘要： A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.
摘要翻译： 提供涡轮发动机定子叶片，其围绕轴线旋转，并且包括翼型件，凸缘和轴。 机翼在第一翼型端和第二翼型端之间轴向延伸。 翼型件包括凹面侧面，凸面侧面和空腔。 凹面和凸面侧面在翼型前缘和翼型后缘之间延伸。 空腔从第二翼型端的端面中的腔入口轴向延伸到翼型中。 法兰连接到第二翼型端。 凸缘围绕空腔入口的至少一部分周向延伸，并且从凹入和凸出的侧表面径向地远离到远侧凸缘边缘。 轴沿轴线延伸，并连接到第二翼型端。
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公开(公告)号：US08911208B2
公开(公告)日：2014-12-16
申请号：US13440167
申请日：2012-04-05
申请人： Tracy A. Propheter-Hinckley , Justin D. Piggush , Yongxiang D. Xue , Amarnath Ramlogan , Anthony P. Cherolis , Matthew A. Devore , Eric P. Letizia
发明人： Tracy A. Propheter-Hinckley , Justin D. Piggush , Yongxiang D. Xue , Amarnath Ramlogan , Anthony P. Cherolis , Matthew A. Devore , Eric P. Letizia
CPC分类号： F01D5/187 , B22C7/00 , B22C7/02 , B22C9/043 , B22C9/10 , B22C9/103 , B22C9/24 , B22D25/06 , F01D5/147 , F01D5/18 , F01D5/3007 , F05D2230/21 , F05D2300/13 , F05D2300/611 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.
摘要翻译： 该图案具有图案材料和铸造芯组合。 图案材料具有翼型。 铸造芯组合至少部分地嵌入图案材料中。 铸造芯组合包括金属铸造芯和至少一个另外的铸芯。 金属铸造芯具有相对的第一和第二面。 金属芯和至少一个额外的铸芯将翼展方向延伸到图案材料的翼型中。 在图案材料的翼型外部的图案材料的至少一部分中，金属铸造芯横向于翼展方向弯曲，以便至少部分地围绕至少一个附加铸芯的相邻部分。
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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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