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公开(公告)号：US20100293957A1
公开(公告)日：2010-11-25
申请号：US12468724
申请日：2009-05-19
申请人： Wei Chen , Jesse Edwin Trout , Jeffrey Lebegue
发明人： Wei Chen , Jesse Edwin Trout , Jeffrey Lebegue
CPC分类号： F01D9/023 , F01D25/12 , F05D2230/90 , F05D2250/192 , F05D2260/201 , F23R3/04 , Y02T50/67 , Y02T50/676
摘要： A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening on a hot-side, and a section of thermal barrier coating (TBC) applied on the cold-side and having an opening that generally circumscribes the first opening.
摘要翻译： 在一个实施例中，系统包括发动机壁。 发动机壁包括冷侧和热侧。 发动机壁包括一个或多个稀释孔，其中一个或多个稀释孔中的每一个包括冷侧上的第一开口，热侧上的第二开口和施加在热侧上的热屏障涂层（TBC） 冷侧并且具有通常限定第一开口的开口。
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公开(公告)号：US08397511B2
公开(公告)日：2013-03-19
申请号：US12468724
申请日：2009-05-19
申请人： Wei Chen , Jesse Edwin Trout , Jeffrey Lebegue
发明人： Wei Chen , Jesse Edwin Trout , Jeffrey Lebegue
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2230/90 , F05D2250/192 , F05D2260/201 , F23R3/04 , Y02T50/67 , Y02T50/676
摘要： A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening on a hot-side, and a section of thermal barrier coating (TBC) applied on the cold-side and having an opening that generally circumscribes the first opening.
摘要翻译： 在一个实施例中，系统包括发动机壁。 发动机壁包括冷侧和热侧。 发动机壁包括一个或多个稀释孔，其中一个或多个稀释孔中的每一个包括冷侧上的第一开口，热侧上的第二开口和施加在热侧上的热屏障涂层（TBC） 冷侧并且具有通常限定第一开口的开口。
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公开(公告)号：US08038382B2
公开(公告)日：2011-10-18
申请号：US12775566
申请日：2010-05-07
CPC分类号： F01D11/20 , F01D11/24 , F05D2260/80 , F05D2270/303
摘要： Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.
摘要翻译： 提供了用于控制燃气轮机间隙的系统和方法。 可以确定燃气轮机的轴的温度，并且可以基于轴的温度来确定涡轮机的内涡轮壳体的期望温度。 内涡轮壳体的期望温度可以与涡轮机间隙相关联，在那里可以点燃燃气涡轮机。 可以通过控制在内涡轮机壳体内循环的气体的温度来改变内涡轮机壳体的温度，并且可以确定内涡轮机壳体的温度超过所需温度。 在确定内涡轮壳体的温度超过所需温度之后，可以点燃燃气轮机。
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公开(公告)号：US20100218506A1
公开(公告)日：2010-09-02
申请号：US12775566
申请日：2010-05-07
IPC分类号： F02C1/00
CPC分类号： F01D11/20 , F01D11/24 , F05D2260/80 , F05D2270/303
摘要： Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.
摘要翻译： 提供了用于控制燃气轮机间隙的系统和方法。 可以确定燃气轮机的轴的温度，并且可以基于轴的温度来确定涡轮机的内涡轮壳体的期望温度。 内涡轮壳体的期望温度可以与涡轮机间隙相关联，在那里可以点燃燃气涡轮机。 可以通过控制在内涡轮机壳体内循环的气体的温度来改变内涡轮机壳体的温度，并且可以确定内涡轮机壳体的温度超过所需温度。 在确定内涡轮壳体的温度超过所需温度之后，可以点燃燃气轮机。
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公开(公告)号：US20080069683A1
公开(公告)日：2008-03-20
申请号：US11532302
申请日：2006-09-15
IPC分类号： F04D27/02
CPC分类号： F01D11/20 , F01D11/24 , F05D2260/80 , F05D2270/303
摘要： A method and system for controlling the clearance in a gas turbine. The current clearance between a turbine blade and a casing of the gas turbine is determined. Then, a determination is made as to whether the current clearance is within a predetermined clearance threshold and a control action is taken if the current clearance is outside of the predetermined clearance threshold.
摘要翻译： 一种用于控制燃气轮机间隙的方法和系统。 确定涡轮机叶片和燃气涡轮机壳体之间的当前间隙。 然后，确定当前间隙是否处于预定间隙阈值内，并且如果当前间隙超出预定间隙阈值，则进行控制动作。
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