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11. 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。

12. 发明授权

US09249674B2 Turbine rotor blade platform cooling 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US09249674B2
公开(公告)日：2016-02-02
申请号：US13341024
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform positioned between an airfoil and a root. The rotor blade, along a side that coincides with a pressure side of the airfoil, includes a pressure side of the platform includes a topside extending from an airfoil base to a pressure side slashface. The platform cooling arrangement includes: a main plenum residing just inboard of the topside in the pressure side of the platform, the main plenum extending through the platform from an upstream end having an aft position to a downstream end having a forward position; and cooling apertures. Near the upstream end, the main plenum includes an aft switchback, and, between the aft switchback and the downstream end, a forward arc. Each of the cooling apertures extends from the main plenum to a port formed on the pressure side slashface.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有位于翼型件和根部之间的平台。转子叶片沿着与翼型件的压力侧重合的一侧，包括平台的压力侧，其包括从翼型基部延伸到压力侧斜面的顶侧。平台冷却装置包括：位于平台的压力侧的顶侧刚好内侧的主增压室，主增压室从具有后位的上游端延伸穿过平台到具有向前位置的下游端; 和冷却孔。在上游端附近，主增压室包括尾部折返，并且在后退和下游端之间具有前弧。每个冷却孔从主增压室延伸到形成在压力侧斜面上的端口。

13. 发明申请

US20140064983A1 AIRFOIL AND METHOD FOR MANUFACTURING AN AIRFOIL 审中-公开
标题翻译：飞行器和制造航空器的方法
公开(公告)号：US20140064983A1
公开(公告)日：2014-03-06
申请号：US13600717
申请日：2012-08-31
申请人： Mark Andrew Jones , Aaron Ezekiel Smith , Harika Senem Kahveci
发明人： Mark Andrew Jones , Aaron Ezekiel Smith , Harika Senem Kahveci
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/304 , F05D2260/202
摘要： An airfoil includes a pressure side, a suction side opposed to the pressure side, a cavity inside the airfoil between the pressure and suction sides, and a trailing edge downstream from the cavity between the pressure and suction sides. A first set of cooling passages through the trailing edge provide fluid communication from the cavity through the trailing edge. A first divider across each cooling passage in the first set of cooling passages extends from the pressure side to the suction side at the trailing edge.
摘要翻译：翼型件包括压力侧，与压力侧相对的吸入侧，在压力侧和吸力侧之间的翼型内的空腔，以及在压力侧和吸力侧之间的空腔下游的后缘。通过后缘的第一组冷却通道提供从空腔到后缘的流体连通。第一组冷却通道中的每个冷却通道的第一分隔件从后侧的压力侧延伸到吸入侧。

14. 发明申请

US20130171003A1 TURBINE ROTOR BLADE PLATFORM COOLING 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US20130171003A1
公开(公告)日：2013-07-04
申请号：US13341018
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement for a turbine rotor blade having a platform at an interface between an airfoil and a root, the root including attachment means and a shank, wherein the platform comprises a suction side that includes a topside extending from an airfoil base to a suction side slashface, and wherein the platform overhangs a shank cavity. The platform cooling arrangement may include: a pocket formed in an underside region of the platform, the pocket comprising a mouth that fluidly communicates with the shank cavity; a manifold extending from the suction side slashface to a pressure side slashface, the manifold including a connection to the pocket; and cooling apertures that extend from connections made with the pocket and manifold to ports.
摘要翻译：一种用于涡轮转子叶片的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，所述根部包括附接装置和柄部，其中所述平台包括吸力侧，所述吸力侧包括从翼型基部到吸力侧斜面，并且其中所述平台突出于柄空腔。平台冷却装置可以包括：形成在平台的下侧区域中的口袋，所述口袋包括与所述柄腔流体连通的口; 歧管从吸力侧斜面延伸到压力侧斜面，歧管包括与口袋的连接; 以及从由袋和歧管制成的连接件延伸到端口的冷却孔。

15. 发明申请

US20130052035A1 AXIALLY COOLED AIRFOIL 审中-公开
标题翻译： AXIALLY冷却空气
公开(公告)号：US20130052035A1
公开(公告)日：2013-02-28
申请号：US13216403
申请日：2011-08-24
申请人： Sandip Dutta , Aaron Ezekiel Smith
发明人： Sandip Dutta , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/311 , F05D2260/221
摘要： An airfoil is provided. The airfoil includes an airfoil blade. The airfoil blade has a trailing edge, a pressure sidewall and a suction sidewall, where a portion of the airfoil blade has a widest cross section when measured between the suction sidewall and the pressure sidewall. A plenum is located along the widest cross section. At least one passageway extends in an axial direction from the plenum and terminates at the trailing edge. The at least one passageway is in fluid communication with and receives a flow from the plenum.
摘要翻译：提供翼型。翼型件包括翼型叶片。翼型叶片具有后缘，压力侧壁和抽吸侧壁，其中当在吸力侧壁和压力侧壁之间测量时翼型叶片的一部分具有最宽的横截面。最广泛的横断面设有一个会议厅。至少一个通道从气室沿轴向延伸并终止在后缘。至少一个通道与气室流体连通并接收来自气室的流体。

16. 发明申请

US20140069110A1 TURBINE BUCKET INTERNAL CORE PROFILE 有权
标题翻译： TURBINE BUCKET内芯轮廓
公开(公告)号：US20140069110A1
公开(公告)日：2014-03-13
申请号：US13613922
申请日：2012-09-13
申请人： Randall Richard Good , Bradley Taylor Boyer , Xiaoyong Fu , Aaron Ezekiel Smith , Jacob C. Perry, II
发明人： Randall Richard Good , Bradley Taylor Boyer , Xiaoyong Fu , Aaron Ezekiel Smith , Jacob C. Perry, II
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/187
摘要： Turbine bucket nominal internal core profiles and core insert external profiles are provided. In one embodiment, a turbine bucket includes an airfoil, platform, shank and dovetail. The bucket has a nominal internal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are non-dimensional values which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.
摘要翻译：提供涡轮桶标称内芯型材和芯插件外部型材。在一个实施例中，涡轮机桶包括翼型件，平台，柄和燕尾榫。铲斗具有基本上根据表1所示的X，Y和Z的笛卡尔坐标值的标称内部芯轮廓，其中Z值是从0到1的无量纲值，可以通过将Z值乘以Z 以铲斗的高度为英寸，其中X和Y为无量纲值，当通过平滑连续的圆弧连接时，沿着铲斗在每个距离Z处限定内芯轮廓部分，Z距离处的轮廓部分被连接彼此平滑地形成所述桶内芯轮廓。

17. 发明申请

US20140069108A1 BUCKET ASSEMBLY FOR TURBOMACHINE 审中-公开
标题翻译：用于涡轮发动机的水箱总成
公开(公告)号：US20140069108A1
公开(公告)日：2014-03-13
申请号：US13606404
申请日：2012-09-07
申请人： Randall Richard Good , Gary Michael Itzel , Aaron Ezekiel Smith
发明人： Randall Richard Good , Gary Michael Itzel , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187
摘要： Bucket assemblies are provided. The bucket assembly includes a shank, and an airfoil positioned radially outward of the shank. The bucket assembly further includes a main cooling circuit defined in the airfoil and the shank, the main cooling circuit comprising seven passages, each of the seven passages fluidly connected with an adjacent one of the seven passages. A maximum rotation number in each of the seven passages is less than or equal to approximately 0.4.
摘要翻译：提供铲斗组件。铲斗组件包括柄和位于柄的径向外侧的翼型。铲斗组件还包括限定在翼型件和柄部中的主冷却回路，主冷却回路包括七个通道，七个通道中的每一个与七个通道中的相邻一个流体连接。七个通道中的每一个中的最大转数小于或等于大约0.4。

18. 发明申请

US20130115090A1 TURBOMACHINE COMPONENT AND METHOD OF CONNECTING COOLING CIRCUITS OF A TURBOMACHINE COMPONENT 有权
标题翻译：涡轮机组件和连接涡轮机组件的冷却电路的方法
公开(公告)号：US20130115090A1
公开(公告)日：2013-05-09
申请号：US13291759
申请日：2011-11-08
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/14 , B21K25/00
CPC分类号： F02C7/12 , F01D5/081 , F01D5/18 , F05D2240/81 , Y10T29/49321
摘要： A turbomachine component is provided and includes a turbine blade, which is rotatable about a rotor of a turbine for power generation operations and a platform with which the turbine blade is to be assembled. The turbine blade is formed to define a main circuit having an appendage. The platform is formed to define a platform circuit, and a substantially radially extendible pathway configured to be coupled to the appendage and to the platform circuit.
摘要翻译：提供了一种涡轮机组件，其包括涡轮机叶片，该涡轮机叶片可围绕用于发电操作的涡轮机的转子旋转，以及与该涡轮机叶片组装的平台。涡轮叶片形成为限定具有附属物的主电路。平台形成为限定平台电路，以及被配置为耦合到附件和平台电路的基本可径向延伸的通道。

19. 发明授权

US09249673B2 Turbine rotor blade platform cooling 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US09249673B2
公开(公告)日：2016-02-02
申请号：US13341018
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement for a turbine rotor blade having a platform at an interface between an airfoil and a root, the root including attachment means and a shank, wherein the platform comprises a suction side that includes a topside extending from an airfoil base to a suction side slashface, and wherein the platform overhangs a shank cavity. The platform cooling arrangement may include: a pocket formed in an underside region of the platform, the pocket comprising a mouth that fluidly communicates with the shank cavity; a manifold extending from the suction side slashface to a pressure side slashface, the manifold including a connection to the pocket; and cooling apertures that extend from connections made with the pocket and manifold to ports.
摘要翻译：一种用于涡轮转子叶片的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，所述根部包括附接装置和柄部，其中所述平台包括吸力侧，所述吸力侧包括从翼型基部到吸力侧斜面，并且其中所述平台突出于柄空腔。平台冷却装置可以包括：形成在平台的下侧区域中的口袋，所述口袋包括与所述柄腔流体连通的口; 歧管从吸力侧斜面延伸到压力侧斜面，歧管包括与口袋的连接; 以及从由袋和歧管制成的连接件延伸到端口的冷却孔。

20. 发明授权

US09022735B2 Turbomachine component and method of connecting cooling circuits of a turbomachine component 有权
标题翻译：涡轮机组件和连接涡轮机组件冷却回路的方法
公开(公告)号：US09022735B2
公开(公告)日：2015-05-05
申请号：US13291759
申请日：2011-11-08
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18 , F02C7/12 , F01D5/08
CPC分类号： F02C7/12 , F01D5/081 , F01D5/18 , F05D2240/81 , Y10T29/49321
摘要： A turbomachine component is provided and includes a turbine blade, which is rotatable about a rotor of a turbine for power generation operations and a platform with which the turbine blade is to be assembled. The turbine blade is formed to define a main circuit having an appendage. The platform is formed to define a platform circuit, and a substantially radially extendible pathway configured to be coupled to the appendage and to the platform circuit.
摘要翻译：提供了一种涡轮机组件，其包括涡轮机叶片，该涡轮机叶片可围绕用于发电操作的涡轮机的转子旋转，以及与该涡轮机叶片组装的平台。涡轮叶片形成为限定具有附属物的主电路。平台形成为限定平台电路，以及被配置为耦合到附件和平台电路的基本可径向延伸的通道。

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