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公开(公告)号：US20130175357A1
公开(公告)日：2013-07-11
申请号：US13345776
申请日：2012-01-09
申请人： Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
发明人： Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC分类号： F01D11/001 , F05D2240/128 , F05D2260/201
摘要： The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
摘要翻译： 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
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公开(公告)号：US08944751B2
公开(公告)日：2015-02-03
申请号：US13345776
申请日：2012-01-09
申请人： Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
发明人： Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC分类号： F01D11/001 , F05D2240/128 , F05D2260/201
摘要： The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
摘要翻译： 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
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公开(公告)号：US09011079B2
公开(公告)日：2015-04-21
申请号：US13345781
申请日：2012-01-09
申请人： Robert Walter Coign , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Glen Arthur MacMillan , Aaron Gregory Winn
发明人： Robert Walter Coign , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Glen Arthur MacMillan , Aaron Gregory Winn
CPC分类号： F01D5/188 , F01D9/065 , F05D2260/201 , Y02T50/676
摘要： The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.
摘要翻译： 本申请提供了一种划分的冷却系统，用于在涡轮机中提供其中具有燃烧气体流的冷却流。 隔室冷却系统可包括涡轮喷嘴和冷却挡板。 涡轮喷嘴可以包括翼型件插入件和喷嘴外侧壁。 冷却挡板可以包括与第一回路中的翼型插入件连通的高压冷却通道和在第二回路中围绕喷嘴外侧壁定位的冲击板。
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公开(公告)号：US20130177384A1
公开(公告)日：2013-07-11
申请号：US13345781
申请日：2012-01-09
申请人： Robert Walter Coign , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Glen Arthur MacMillan , Aaron Gregory Winn
发明人： Robert Walter Coign , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Glen Arthur MacMillan , Aaron Gregory Winn
CPC分类号： F01D5/188 , F01D9/065 , F05D2260/201 , Y02T50/676
摘要： The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.
摘要翻译： 本申请提供了一种划分的冷却系统，用于在涡轮机中提供其中具有燃烧气体流的冷却流。 隔室冷却系统可包括涡轮喷嘴和冷却挡板。 涡轮喷嘴可以包括翼型件插入件和喷嘴外侧壁。 冷却挡板可以包括与第一回路中的翼型插入件连通的高压冷却通道和在第二回路中围绕喷嘴外侧壁定位的冲击板。
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公开(公告)号：US20130177383A1
公开(公告)日：2013-07-11
申请号：US13343911
申请日：2012-01-05
IPC分类号： F01D11/08
CPC分类号： F01D11/005
摘要： A device for sealing a gas path in a turbine includes a first shroud segment and a slot in a surface of the first shroud segment. A barrier extends inside the slot, and a bypass channel in the slot provides fluid communication between the barrier and the slot to the gas path in the turbine. A method for sealing a gas path in a turbine includes placing a barrier between a first slot in a first shroud segment and a second slot in a second shroud segment and flowing a fluid between the barrier and the first slot to the gas path in the turbine, wherein the fluid flows through a first bypass channel in the first slot.
摘要翻译： 用于密封涡轮机中的气体路径的装置包括第一护罩段和第一护罩区段的表面中的槽。 障碍物在狭槽内部延伸，并且槽中的旁通通道提供阻挡层和槽之间到涡轮机中的气体路径的流体连通。 用于密封涡轮机中的气体路径的方法包括在第一护罩区段中的第一狭槽和第二护罩区段中的第二狭槽之间放置障碍物，并且将阻挡物和第一狭缝之间的流体流动到涡轮机中的气体路径 ，其中所述流体流过所述第一槽中的第一旁通通道。
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公开(公告)号：US08371800B2
公开(公告)日：2013-02-12
申请号：US12716784
申请日：2010-03-03
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/81
摘要： A segment of a component for use in a gas turbine includes a leading edge; a trailing edge; a pair of opposed lateral sides between the leading and trailing edges; and a seal slot provided in each lateral side. The seal slot includes a surface having a channel extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet to the channel, and at least one outlet from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment.
摘要翻译： 用于燃气涡轮机的部件的一部分包括前缘; 后缘 在前缘和后缘之间的一对相对的侧面; 以及设置在每个侧面中的密封槽。 密封槽包括具有沿着从前缘到后缘限定的轴向方向延伸的通道的表面，到通道的至少一个入口和从通道的至少一个出口。 至少一个出口在轴向方向上与至少一个入口的下游间隔开。 该段可以是内部护罩区段或喷嘴区段。
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