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1. 发明授权

US09243510B2 Floating seal 有权
标题翻译：浮动密封
公开(公告)号：US09243510B2
公开(公告)日：2016-01-26
申请号：US13607847
申请日：2012-09-10
申请人： Matthew Stephen Casavant , Kevin Thomas McGovern
发明人： Matthew Stephen Casavant , Kevin Thomas McGovern
IPC分类号： F01D11/00 , F16J15/02 , F16J15/32
CPC分类号： F01D11/005 , F16J15/3288
摘要： A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value.
摘要翻译：公开了一种用于密封两个静态部件的浮动密封组件。每个静态部分具有相对的槽，并且相对的槽限定密封腔。浮动密封组件包括具有中间部分和相对端部的浮动圆周密封件，每个相对的端部部分位于一个静止部件中的凹槽内，其中每个端部具有面向密封腔的低压侧的弯曲面。根据本发明的实施例的浮动密封组件是压力驱动的，因为端部的每个弯曲侧被构造成响应于跨越密封腔的压差达到阈值而与密封腔的低压侧接合。

2. 发明申请

US20130177383A1 DEVICE AND METHOD FOR SEALING A GAS PATH IN A TURBINE 审中-公开
标题翻译：用于密封涡轮气体路径的装置和方法
公开(公告)号：US20130177383A1
公开(公告)日：2013-07-11
申请号：US13343911
申请日：2012-01-05
申请人： Aaron Gregory Winn , Kevin Thomas McGovern , Ravichandran Meenakshisundaram
发明人： Aaron Gregory Winn , Kevin Thomas McGovern , Ravichandran Meenakshisundaram
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。

3. 发明授权

US08128344B2 Methods and apparatus involving shroud cooling 有权
标题翻译：包括护罩冷却的方法和设备
公开(公告)号：US08128344B2
公开(公告)日：2012-03-06
申请号：US12265315
申请日：2008-11-05
申请人： Kevin Thomas McGovern , Bryan David Lewis , Zachary James Taylor
发明人： Kevin Thomas McGovern , Bryan David Lewis , Zachary James Taylor
IPC分类号： F04D31/00
CPC分类号： F01D11/08 , B23H9/10 , B23H9/14 , F05D2230/12 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , Y10T29/49341
摘要： A turbine cooling component comprising a circumferential leading edge, a circumferential trailing edge, a pair of spaced and opposed side panels connected to the leading and trailing edges, an arcuate base connected to the trailing and leading edges having a fore portion, a midsection portion, an aft portion, opposed side portions, an outer surface partially defining a cavity operative to receive pressurized air, and an arcuate inner surface in contact with a gas flow path of a turbine engine, a first side cooling air passage in the base extending along the first side portion from the fore portion to the aft portion, and a fore cooling air passage in the fore portion of the base communicative with the side cooling air passage and the cavity, operative to receive the pressurized air from the cavity.
摘要翻译：一种涡轮机冷却部件，包括周向前缘，周向后缘，连接到前缘和后缘的一对间隔和相对的侧片，连接到具有前部的后缘和前缘的弧形底座，中央部分，后部部分，相对的侧部，部分地限定用于接收加压空气的空腔的外表面和与涡轮发动机的气体流动路径接触的弓形内表面，所述基部中的第一侧冷却空气通道沿着从前部到后部的第一侧部分，以及与侧面冷却空气通道和空腔相通的基座的前部中的前部冷却空气通道，用于从空腔接收加压空气。

4. 发明申请

US20100111671A1 METHODS AND APPARATUS INVOLVING SHROUD COOLING 有权
标题翻译：涉及冷却的方法和装置
公开(公告)号：US20100111671A1
公开(公告)日：2010-05-06
申请号：US12265315
申请日：2008-11-05
申请人： Kevin Thomas McGovern , Bryan David Lewis , Zachary James Taylor
发明人： Kevin Thomas McGovern , Bryan David Lewis , Zachary James Taylor
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D11/08 , B23H9/10 , B23H9/14 , F05D2230/12 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , Y10T29/49341
摘要： A turbine cooling component comprising a circumferential leading edge, a circumferential trailing edge, a pair of spaced and opposed side panels connected to the leading and trailing edges, an arcuate base connected to the trailing and leading edges having a fore portion, a midsection portion, an aft portion, opposed side portions, an outer surface partially defining a cavity operative to receive pressurized air, and an arcuate inner surface in contact with a gas flow path of a turbine engine, a first side cooling air passage in the base extending along the first side portion from the fore portion to the aft portion, and a fore cooling air passage in the fore portion of the base communicative with the side cooling air passage and the cavity, operative to receive the pressurized air from the cavity.
摘要翻译：一种涡轮机冷却部件，包括周向前缘，周向后缘，连接到前缘和后缘的一对间隔和相对的侧片，连接到具有前部的后缘和前缘的弧形底座，中央部分，后部部分，相对的侧部，部分地限定用于接收加压空气的空腔的外表面和与涡轮发动机的气体流动路径接触的弓形内表面，所述基部中的第一侧冷却空气通道沿着从前部到后部的第一侧部分，以及与侧面冷却空气通道和空腔相通的基座的前部中的前部冷却空气通道，用于从空腔接收加压空气。

5. 发明申请

US20100072710A1 Gas Turbine Seal 审中-公开
标题翻译：燃气轮机密封
公开(公告)号：US20100072710A1
公开(公告)日：2010-03-25
申请号：US12234989
申请日：2008-09-22
申请人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
发明人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
IPC分类号： F16J15/16
CPC分类号： F16J15/0887 , F01D9/042 , F01D11/005 , F05D2220/3212
摘要： A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner.
摘要翻译：提供用于密封燃气涡轮发动机的两个相邻部件的密封件。密封件具有第一和第二密封表面，其操作以密封相邻部件以在其间产生有效的密封。此外，密封件具有第一端和第二端，其中第二端具有颈缩部分，其被构造成以滑动重叠的方式内部接合第一端。

6. 发明申请

US20140072418A1 FLOATING SEAL 有权
标题翻译：浮动密封
公开(公告)号：US20140072418A1
公开(公告)日：2014-03-13
申请号：US13607847
申请日：2012-09-10
申请人： Matthew Stephen Casavant , Kevin Thomas McGovern
发明人： Matthew Stephen Casavant , Kevin Thomas McGovern
IPC分类号： F01D11/00 , F16J15/02
CPC分类号： F01D11/005 , F16J15/3288
摘要： A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value.
摘要翻译：公开了一种用于密封两个静态部件的浮动密封组件。每个静态部分具有相对的槽，并且相对的槽限定密封腔。浮动密封组件包括具有中间部分和相对端部的浮动圆周密封件，每个相对的端部部分位于一个静止部件中的凹槽内，其中每个端部具有面向密封腔的低压侧的弯曲面。根据本发明的实施例的浮动密封组件是压力驱动的，因为端部的每个弯曲侧被构造成响应于跨越密封腔的压差达到阈值而与密封腔的低压侧接合。

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