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1. 发明申请

US20130061600A1 METHOD OF CONTROLLING TEMPERATURE OF GAS TURBINE COMPONENTS USING A COMPRESSED MOISURIZED COOLANT 审中-公开
标题翻译：使用压缩冷凝器控制气体涡轮机组件温度的方法
公开(公告)号：US20130061600A1
公开(公告)日：2013-03-14
申请号：US13230983
申请日：2011-09-13
申请人： Ashok Kumar Anand , Gary Michael Itzel , Benjamin Paul Lacy , Veerappan Muthaiah , Nagarjuna Reddy Thirumala Reddy
发明人： Ashok Kumar Anand , Gary Michael Itzel , Benjamin Paul Lacy , Veerappan Muthaiah , Nagarjuna Reddy Thirumala Reddy
IPC分类号： F02C7/12 , F02C6/08
CPC分类号： F02C7/18 , F01D5/08 , F01D25/12 , F05D2260/212 , F05D2260/213 , Y02E20/16 , Y02E20/18
摘要： A method and apparatus for controlling a temperature a component of a gas turbine is disclosed. A compressed gas for use as a coolant is provided. The coolant is moisturized at a moisturizeing unit. A circulating unit circulates the moisturized coolant to the component of the gas turbine to control the temperature of the component. The coolant can be air, nitrogen, and a mixture of air and nitrogen in various embodiments. The component of the turbine can be a blade of a turbine section of the gas turbine, a turbine nozzle and a combustor, for example. A combustor can combust a mixture of fuel and the moisturized compressed coolant gas to reduce a NOx emission of the gas turbine.
摘要翻译：公开了一种用于控制燃气轮机的部件的温度的方法和装置。提供用作冷却剂的压缩气体。冷却液在保湿单元中保湿。循环单元将保湿的冷却剂循环到燃气轮机的组件以控制部件的温度。在各种实施例中，冷却剂可以是空气，氮气和空气和氮气的混合物。涡轮机的部件可以是例如燃气轮机的涡轮部分的叶片，涡轮喷嘴和燃烧器。燃烧器可以燃烧燃料和保湿的压缩冷却剂气体的混合物，以减少燃气轮机的NOx排放。

2. 发明申请

US20130115103A1 FILM HOLE TRENCH 有权
标题翻译：电影孔
公开(公告)号：US20130115103A1
公开(公告)日：2013-05-09
申请号：US13292432
申请日：2011-11-09
申请人： Sandip Dutta , Gary Michael Itzel , Benjamin Paul Lacy
发明人： Sandip Dutta , Gary Michael Itzel , Benjamin Paul Lacy
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , Y10T29/49336
摘要： An article is disclosed that comprises a thermal material having a first surface and a second surface. The thermal material defines a film hole between the first surface and the second surface, and the film hole includes a metering portion adjacent the first surface and a diffuser portion adjacent the second surface. The metering portion defines a metering hole axis, and the diffuser portion defines a trench. The trench extends substantially parallel to a metering hole axis.
摘要翻译：公开了一种包括具有第一表面和第二表面的热材料的制品。热材料在第一表面和第二表面之间限定一个薄膜孔，薄膜孔包括邻近第一表面的计量部分和邻近第二表面的扩散器部分。计量部分限定计量孔轴，并且扩散器部分限定沟槽。沟槽基本上平行于计量孔轴线延伸。

3. 发明授权

US08523527B2 Apparatus for cooling a platform of a turbine component 有权
标题翻译：用于冷却涡轮机部件的平台的装置
公开(公告)号：US08523527B2
公开(公告)日：2013-09-03
申请号：US12721040
申请日：2010-03-10
申请人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
发明人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component including a platform and an airfoil extending radially upward from the platform. A plurality of curved cooling passages may be defined in the platform. Each of the curved cooling passages may have at least one end disposed at an exterior surface of the platform. Additionally, each of the cooling passages may be configured to direct a cooling medium through the platform.
摘要翻译：本主题公开了一种涡轮机部件，包括平台和从平台径向向上延伸的翼型件。可以在平台中限定多个弯曲的冷却通道。每个弯曲的冷却通道可以具有设置在平台的外表面的至少一个端部。此外，每个冷却通道可构造成引导冷却介质通过平台。

4. 发明授权

US08858175B2 Film hole trench 有权
标题翻译：电影孔沟
公开(公告)号：US08858175B2
公开(公告)日：2014-10-14
申请号：US13292432
申请日：2011-11-09
申请人： Sandip Dutta , Gary Michael Itzel , Benjamin Paul Lacy
发明人： Sandip Dutta , Gary Michael Itzel , Benjamin Paul Lacy
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/186 , Y10T29/49336
摘要： An article is disclosed that comprises a thermal material having a first surface and a second surface. The thermal material defines a film hole between the first surface and the second surface, and the film hole includes a metering portion adjacent the first surface and a diffuser portion adjacent the second surface. The metering portion defines a metering hole axis, and the diffuser portion defines a trench. The trench extends substantially parallel to a metering hole axis.
摘要翻译：公开了一种包括具有第一表面和第二表面的热材料的制品。热材料在第一表面和第二表面之间限定一个薄膜孔，薄膜孔包括邻近第一表面的计量部分和邻近第二表面的扩散器部分。计量部分限定计量孔轴，并且扩散器部分限定沟槽。沟槽基本上平行于计量孔轴线延伸。

5. 发明申请

US20110259017A1 HOT GAS PATH COMPONENT COOLING SYSTEM 有权
标题翻译：热气路成分冷却系统
公开(公告)号：US20110259017A1
公开(公告)日：2011-10-27
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F02C7/12 , F28F13/18
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

6. 发明授权

US08651805B2 Hot gas path component cooling system 有权
标题翻译：热气路组件冷却系统
公开(公告)号：US08651805B2
公开(公告)日：2014-02-18
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D25/14
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

7. 发明申请

US20110223004A1 APPARATUS FOR COOLING A PLATFORM OF A TURBINE COMPONENT 有权
标题翻译：用于冷却涡轮机组件平台的装置
公开(公告)号：US20110223004A1
公开(公告)日：2011-09-15
申请号：US12721040
申请日：2010-03-10
申请人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
发明人： Benjamin Paul Lacy , Gary Michael Itzel , Bin Wei
IPC分类号： F02C7/12
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component including a platform and an airfoil extending radially upward from the platform. A plurality of curved cooling passages may be defined in the platform. Each of the curved cooling passages may have at least one end disposed at an exterior surface of the platform. Additionally, each of the cooling passages may be configured to direct a cooling medium through the platform.
摘要翻译：本主题公开了一种涡轮机部件，包括平台和从平台径向向上延伸的翼型件。可以在平台中限定多个弯曲的冷却通道。每个弯曲的冷却通道可以具有设置在平台的外表面的至少一个端部。此外，每个冷却通道可构造成引导冷却介质通过平台。

8. 发明授权

US09376931B2 Turbomachine passage cleaning system 有权
标题翻译：涡轮机通道清洗系统
公开(公告)号：US09376931B2
公开(公告)日：2016-06-28
申请号：US13359962
申请日：2012-01-27
申请人： Arun Meenakshinatha Iyer , Douglas Scott Byrd , Gary Michael Itzel , Jaime Javier Maldonado
发明人： Arun Meenakshinatha Iyer , Douglas Scott Byrd , Gary Michael Itzel , Jaime Javier Maldonado
IPC分类号： F04D29/58 , F01D25/00
CPC分类号： F01D25/002 , F04D29/5846 , F05D2210/13 , F05D2260/2322 , F05D2260/607
摘要： A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.
摘要翻译：涡轮机通道清洁系统包括第一气流通道，其具有构造和设置成流体连接到压缩机部分的第一入口，被配置和设置成流体连接到涡轮机部分的第一出口和包括第一过滤器的第一中间部分。第二气流通道流体地联接到第一气流通道。第二气流通道具有具有第二过滤器的第二中间部分。第一阀布置在第一过滤器上游的第一中间部分中，并且第二阀布置在第二过滤器上游的第二中间部分中。选择性地操作第一阀和第二阀以控制流入第一和第二气流通道中的相应流体的流体，以过滤从涡轮机压缩机部分流到涡轮机涡轮机部分的空气。

9. 发明授权

US09175565B2 Systems and apparatus relating to seals for turbine engines 有权
标题翻译：与涡轮发动机密封相关的系统和设备
公开(公告)号：US09175565B2
公开(公告)日：2015-11-03
申请号：US13566189
申请日：2012-08-03
申请人： Christopher Donald Porter , Gary Michael Itzel
发明人： Christopher Donald Porter , Gary Michael Itzel
IPC分类号： F01D5/08 , F01D11/00 , F01D11/04
CPC分类号： F01D5/081 , F01D11/001 , F01D11/04 , F05D2240/55 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.
摘要翻译：描述了燃气涡轮发动机的涡轮机中的密封件。密封件形成在限定在转子叶片和定子叶片之间的沟槽腔内。定子叶片包括侧壁突起，转子叶片包括向定子叶片延伸的天使翼突起。侧壁突起悬挂天使翼投影。密封件包括：设置在定子突起的内表面上的端口; 以及设置在天使翼突起上的偏转结构。偏转结构可以被配置为接收从端口排出的流体并使流体朝向沟槽腔的入口偏转。

10. 发明授权

US08967957B2 Rotating airfoil component of a turbomachine 有权
标题翻译：涡轮机的旋翼型部件
公开(公告)号：US08967957B2
公开(公告)日：2015-03-03
申请号：US13288100
申请日：2011-11-03
申请人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
发明人： Gary Michael Itzel , Christopher Michael Penny , Aaron Ezekiel Smith , Kevin Leon Bruce
IPC分类号： F04D29/08 , F01D11/02 , F01D5/28
CPC分类号： F01D11/02 , F01D5/288 , Y02T50/671
摘要： A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.
摘要翻译：装备有一个或多个天使翼的旋转翼型零件，其阻止热工作流体进入其中安装该部件的涡轮机的内部区域。该部件包括翼型件和用于安装部件以使部件在涡轮机内旋转的特征。天使翼从部件突出以具有面向翼型的第一表面，面对安装特征的相对设置的第二表面以及其间的至少一个侧表面。绝热涂层系统存在于第一表面上以抑制从工作流体传递到天使翼而不是在第二或侧面上的热传递，从而不会妨碍从天使翼的第二和侧面的热传递。

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