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1. 发明授权

US09297262B2 Cooling structures in the tips of turbine rotor blades 有权
标题翻译：涡轮转子叶片尖端的冷却结构
公开(公告)号：US09297262B2
公开(公告)日：2016-03-29
申请号：US13479683
申请日：2012-05-24
申请人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
发明人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/20 , F01D5/186
摘要： A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface.
摘要翻译：描述了一种用于燃气涡轮发动机的涡轮转子叶片。涡轮转子叶片包括在外径向端部包括尖端的翼型件。尖端包括限定尖端腔的轨道; 并且轨道包括外接轨道微通道。外接导轨微通道是围绕内轨表面的至少大部分长度延伸的微通道。

2. 发明申请

US20130315749A1 COOLING STRUCTURES IN THE TIPS OF TURBINE ROTOR BLADES 有权
标题翻译：涡轮转子叶片的冷却结构
公开(公告)号：US20130315749A1
公开(公告)日：2013-11-28
申请号：US13479683
申请日：2012-05-24
申请人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
发明人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/186
摘要： A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface.
摘要翻译：描述了一种用于燃气涡轮发动机的涡轮转子叶片。涡轮转子叶片包括在外径向端部包括尖端的翼型件。尖端包括限定尖端腔的轨道; 并且轨道包括外接轨道微通道。外接导轨微通道是围绕内轨表面的至少大部分长度延伸的微通道。

3. 发明申请

US20130039758A1 TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL 审中-公开
标题翻译：涡轮机空气和控制涡轮机空气温度的方法
公开(公告)号：US20130039758A1
公开(公告)日：2013-02-14
申请号：US13205763
申请日：2011-08-09
申请人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
IPC分类号： F01D5/18
CPC分类号： F01D11/04 , F01D11/006 , F05D2240/81 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.
摘要翻译：根据本发明的一个方面，涡轮机翼片包括平台和从平台延伸的叶片。翼型件还包括形成在平台的斜面中的槽，该槽被配置为经由通道接收加压流体并且构造成将加压流体引导到涡轮机翼型的选定区域以改善翼型件的寿命。

4. 发明申请

US20130094944A1 BUCKET ASSEMBLY FOR TURBINE SYSTEM 有权
标题翻译：用于涡轮机系统的BUCKET装配
公开(公告)号：US20130094944A1
公开(公告)日：2013-04-18
申请号：US13271751
申请日：2011-10-12
申请人： Benjamin Paul Lacy , Anthony Louis Giglio
发明人： Benjamin Paul Lacy , Anthony Louis Giglio
IPC分类号： F01D11/08
CPC分类号： F01D5/225 , F05D2230/31 , F05D2250/294 , F05D2260/204
摘要： A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.
摘要翻译：公开了一种铲斗组合件。铲斗组件包括具有大致空气动力学轮廓并限定尖端的翼型件和从翼型件大致径向向内延伸的下主体部分。铲斗组件还包括设置在翼型件的尖端上并包括主体和轨道的尖端护罩。导轨包括外表面。外表面限定了一个微通道。铲斗组件还包括构造在外表面上的覆盖层。

5. 发明授权

US08956104B2 Bucket assembly for turbine system 有权
标题翻译：用于涡轮机系统的铲斗总成
公开(公告)号：US08956104B2
公开(公告)日：2015-02-17
申请号：US13271751
申请日：2011-10-12
申请人： Benjamin Paul Lacy , Anthony Louis Giglio
发明人： Benjamin Paul Lacy , Anthony Louis Giglio
IPC分类号： F01D5/08 , F01D11/08 , F01D5/22
CPC分类号： F01D5/225 , F05D2230/31 , F05D2250/294 , F05D2260/204
摘要： A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.
摘要翻译：公开了一种铲斗组合件。铲斗组件包括具有大致空气动力学轮廓并限定尖端的翼型件和从翼型件大致径向向内延伸的下主体部分。铲斗组件还包括设置在翼型件的尖端上并包括主体和轨道的尖端护罩。导轨包括外表面。外表面限定了一个微通道。铲斗组件还包括构造在外表面上的覆盖层。

6. 发明授权

US09127560B2 Cooled turbine blade and method for cooling a turbine blade 有权
标题翻译：冷却涡轮叶片和冷却涡轮叶片的方法
公开(公告)号：US09127560B2
公开(公告)日：2015-09-08
申请号：US13308927
申请日：2011-12-01
申请人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
发明人： Matthew Durham Collier , Anthony Louis Giglio , Gayathri Puram
IPC分类号： F01D5/08 , F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.
摘要翻译：冷却的涡轮叶片包括用于将叶片固定到转子的根部，沿着径向轴线从根部延伸的翼型件，以及设置在翼型件的径向向外端部处的尖端护罩。尖端护罩从翼型件在圆周方向上延伸，并且在其本身内限定出一个内部集气室和一个周边通风室。翼型件限定了靠近翼型件的后缘部分的径向延伸穿过翼型件的后翼型件冷却通道。翼型件还限定了一个后部冷却入口，用于向后翼型冷却通道提供冷却流体的后部流。翼型件还限定至少一个后冷却出口，用于将后流冷却流体从尾气流冷却通道排出到周边通风室。尖端罩限定了至少一个周边通风口，用于排出冷却流体的后部流。

7. 发明申请

US20140044557A1 TURBINE BLADE AND METHOD FOR COOLING THE TURBINE BLADE 审中-公开
标题翻译：涡轮叶片和用于冷却涡轮叶片的方法
公开(公告)号：US20140044557A1
公开(公告)日：2014-02-13
申请号：US13570688
申请日：2012-08-09
申请人： Anthony Louis Giglio , Scott Edmond Ellis , Jesse Blair Butler , Camilo Andres Sampayo
发明人： Anthony Louis Giglio , Scott Edmond Ellis , Jesse Blair Butler , Camilo Andres Sampayo
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/20
摘要： A turbine blade includes an outer surface, and a rim surrounds at least a portion of the outer surface. A trench in the rim extends around at least a portion of the outer surface.
摘要翻译：涡轮叶片包括外表面，并且边缘围绕外表面的至少一部分。边缘中的沟槽围绕外表面的至少一部分延伸。

8. 发明申请

US20120107135A1 APPARATUS, SYSTEMS AND METHODS FOR COOLING THE PLATFORM REGION OF TURBINE ROTOR BLADES 审中-公开
标题翻译：用于冷却涡轮转子叶片平台区域的装置，系统和方法
公开(公告)号：US20120107135A1
公开(公告)日：2012-05-03
申请号：US12915501
申请日：2010-10-29
申请人： John Wesley Harris, JR. , Daniel Howard Tragesser , Anthony Louis Giglio
发明人： John Wesley Harris, JR. , Daniel Howard Tragesser , Anthony Louis Giglio
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends to the approximate radial height of the platform, and wherein, a pressure side of the platform comprises a planar topside that extends circumferentially from the airfoil to a pressure side slashface, and a suction side of the platform comprises a substantially planar topside that extends circumferentially from the airfoil to a suction side slashface. The platform cooling arrangement may include a linear plenum residing just inboard of the planar topside and linearly extending through the platform from either the pressure side slashface or the suction side slashface to a connection with the interior cooling passage, the linear plenum having a longitudinal axis that is approximately parallel to the planar topside; and a plurality of cooling apertures linearly extending from a topside outlet formed on the topside of the platform to a connection with the linear plenum, wherein the cooling apertures are configured such that each forms an acute angle with the topside of the platform.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中转子叶片包括延伸到平台的近似径向高度的内部冷却通道，并且其中，平台包括从翼型件到圆周方向延伸到压力侧斜面的平面顶面，并且平台的吸力侧包括从翼型件周向延伸到吸力侧斜面的基本平坦的顶侧。平台冷却装置可以包括位于平坦顶侧的刚好内侧并且从压力侧斜面或吸力侧斜面直线延伸穿过平台的线性增压室到与内部冷却通道的连接，线性增压室具有纵向轴线，大致平行于平面顶面; 以及多个冷却孔，其从形成在所述平台顶部上的顶部出口线性地延伸到与所述线性压力室的连接，其中所述冷却孔配置成使得每个与所述平台的顶侧形成锐角。

9. 发明授权

US08662849B2 Component of a turbine bucket platform 有权
标题翻译：涡轮斗平台的组件
公开(公告)号：US08662849B2
公开(公告)日：2014-03-04
申请号：US13026873
申请日：2011-02-14
申请人： Anthony Louis Giglio , Sergio Daniel Marques Amaral , Mark Steven Honkomp , Camilo Andres Sampayo
发明人： Anthony Louis Giglio , Sergio Daniel Marques Amaral , Mark Steven Honkomp , Camilo Andres Sampayo
IPC分类号： F01D5/30
CPC分类号： F01D5/288
摘要： A component is provided and includes a first surface, a second surface adjacent to and oriented transversely with respect to the first surface and having a pocket formed therein defining a rib along a periphery thereof and a thermal barrier coating (TBC) respectively applied to the first surface and to the second surface at the pocket such that the rib is interposed between the TBC of the first and second surfaces.
摘要翻译：提供部件，其包括第一表面，与第一表面相邻并相对于第一表面横向定向的第二表面，并且具有形成在其中沿其周边形成肋的凹穴和分别施加到第一表面的隔热涂层（TBC）表面并且在凹穴处的第二表面，使得肋插入在第一和第二表面的TBC之间。

10. 发明申请

US20140023497A1 COOLED TURBINE BLADE TIP SHROUD WITH FILM/PURGE HOLES 审中-公开
标题翻译：冷却涡轮叶片，带有薄膜/普通球
公开(公告)号：US20140023497A1
公开(公告)日：2014-01-23
申请号：US13553151
申请日：2012-07-19
申请人： Anthony Louis Giglio , Michael J. Kline
发明人： Anthony Louis Giglio , Michael J. Kline
IPC分类号： F01D5/18
CPC分类号： F01D5/225 , F05D2260/202
摘要： A cooled turbine blade shroud with purge holes located proximate regions of the tip shroud cooling cavity that experience cooling air flow recirculation or stagnation. The purge holes may be oriented radially from the cooling cavity to a surface, such as the outer top surface and/or inner/bottom surface, of the tip shroud, and may provide improved heat transfer and consequent cooling and enhanced tip shroud life.
摘要翻译：冷却的涡轮机叶片护罩，其具有位于尖端护罩冷却腔的附近的吹扫孔，其经历冷却空气流再循环或停滞。吹扫孔可以从冷却腔径向定向到尖端护罩的表面，例如外顶表面和/或内/底表面，并且可以提供改进的热传递和随之而来的冷却和增强的尖端护罩寿命。

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