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81. 发明申请

US20140037435A1 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装置
公开(公告)号：US20140037435A1
公开(公告)日：2014-02-06
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： F01D11/08
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。

82. 发明授权

US08636471B2 Apparatus and methods for cooling platform regions of turbine rotor blades 有权
标题翻译：涡轮转子叶片冷却平台区域的装置和方法
公开(公告)号：US08636471B2
公开(公告)日：2014-01-28
申请号：US12972835
申请日：2010-12-20
申请人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
发明人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/187 , F01D5/087 , F05D2240/81 , F05D2250/185 , Y02T50/671 , Y02T50/676 , Y10T29/49341
摘要： A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension.
摘要翻译：通过涡轮转子叶片的内部的冷却通道的构造，涡轮转子叶片包括在翼型件和根部之间的界面处的平台。在一个实施例中，冷却通道的构造包括：内部冷却通道，其构造成从与根部中的冷却剂源的连接延伸到翼型件的内部; 平台冷却通道，其横穿所述平台的至少一部分; 包括与所述平台冷却通道的连接的第一部分和包括径向定向的冷却通道的第二部分的调节延伸部; 以及连接器，该连接器从形成为通过根部的外表面的连接器开口延伸到与内部冷却通道的连接，并且在两者之间平分调节延伸部分的第二部分。

83. 发明申请

US20140000287A1 GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE 有权
标题翻译：气体涡轮发动机涡轮风扇气翼剖面
公开(公告)号：US20140000287A1
公开(公告)日：2014-01-02
申请号：US13539917
申请日：2012-07-02
申请人： Brandon W. Spangler , Russell J. Bergman
发明人： Brandon W. Spangler , Russell J. Bergman
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes, wherein one of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。内部和外部平台分别包括内部和外部薄膜冷却孔组，其中内部和外部薄膜冷却孔组中的一个基本上与基于以下的笛卡尔坐标系中的一组所描述的平台冷却孔位置形成：表1和2.相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供。表1和表2中笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。

84. 发明申请

US20140000285A1 GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE 有权
标题翻译：气体涡轮发动机涡轮风扇平台核心
公开(公告)号：US20140000285A1
公开(公告)日：2014-01-02
申请号：US13539842
申请日：2012-07-02
申请人： Russell J. Bergman , Leonard A. Bach , Brandon W. Spangler
发明人： Russell J. Bergman , Leonard A. Bach , Brandon W. Spangler
IPC分类号： F01D9/02 , F02C7/12
CPC分类号： F01D9/02 , B22C9/04 , B22C9/10 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2230/21 , F05D2230/211 , F05D2240/81 , F05D2250/185 , F05D2260/2214 , Y02T50/672 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。翼型件包括翼型件冷却通道。平台冷却通道布置在内平台和外平台中的至少一个中。平台冷却通道包括多个冷却区域，其中一个冷却区域布置在翼型冷却通道下方。

85. 发明申请

US20140000262A1 GAS TURBINE ENGINE COMPONENT WITH DISCHARGE SLOT HAVING OVAL GEOMETRY 审中-公开
标题翻译：气体涡轮发动机组件与排放槽具有OVAL几何
公开(公告)号：US20140000262A1
公开(公告)日：2014-01-02
申请号：US13598988
申请日：2012-08-30
申请人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
发明人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
IPC分类号： F01D9/02 , F02C3/06
CPC分类号： F01D5/187 , F01D9/065 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/81 , F05D2250/14
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间延伸的主体部分。前缘和后缘中的至少一个包括具有包括椭圆形几何形状的第一部分的至少一个排出槽。

86. 发明申请

US20130318982A1 TURBINE COOLING APPARATUS 审中-公开
标题翻译：涡轮冷却装置
公开(公告)号：US20130318982A1
公开(公告)日：2013-12-05
申请号：US13483613
申请日：2012-05-30
申请人： Yong Weon Kim
发明人： Yong Weon Kim
IPC分类号： F02C7/12 , F01D5/20 , F01D5/18 , F02C3/04
CPC分类号： F01D5/081 , F05D2240/81 , F05D2260/2212 , F05D2260/22141
摘要： The present disclosure describes a turbine blade for a turbine section of a gas turbine engine. The turbine blade includes an airfoil, a platform extending from one side of the airfoil, a root extending from the platform, and at least one purging fin. The at least one purging fin is connected to the root and an underside of the platform, and the at least one purging fin extends along a wall of the root.
摘要翻译：本公开描述了一种用于燃气涡轮发动机的涡轮机部分的涡轮机叶片。涡轮叶片包括翼型件，从翼型件的一侧延伸的平台，从平台延伸的根部和至少一个清洗翼片。所述至少一个清洗翅片连接到所述平台的根部和下侧，并且所述至少一个清洗翅片沿着所述根部的壁延伸。

87. 发明申请

US20130312941A1 COMPONENTS WITH MICROCHANNEL COOLED PLATFORMS AND FILLETS AND METHODS OF MANUFACTURE 有权
标题翻译：具有微通道冷却平台和薄膜的组件及其制造方法
公开(公告)号：US20130312941A1
公开(公告)日：2013-11-28
申请号：US13478517
申请日：2012-05-23
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F28F13/18 , B21D53/02
CPC分类号： F01D5/187 , F01D5/288 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A component includes a substrate that has outer and inner surfaces. The inner surface defines at least one hollow, interior space. The outer surface defines pressure and suction sidewalls that are joined together at leading and trailing edges of the component and together form an airfoil portion of the component. The outer substrate surface further defines at least one platform and at least one fillet that extends between and integrally connects the airfoil to the respective platform. The outer surface defines one or more grooves that extend at least partially along a respective fillet. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface and including at least a structural coating that extends over the groove(s). The groove(s) and the structural coating together define channel(s) for cooling the respective fillet.
摘要翻译：组件包括具有外表面和内表面的基底。内表面限定至少一个中空的内部空间。外表面限定压力和抽吸侧壁，其在部件的前缘和后缘处连接在一起并且一起形成部件的翼型部分。外基材表面进一步限定至少一个平台和至少一个在所述翼型件之间延伸并且将翼片整体连接到相应的平台的圆角。外表面限定了至少部分地沿着相应的圆角延伸的一个或多个凹槽。每个槽与相应的中空的内部空间流体连通。该部件还包括设置在外部基底表面的至少一部分上的涂层，并且至少包括在凹槽上延伸的结构涂层。沟槽和结构涂层一起限定用于冷却相应圆角的通道。

88. 发明授权

US08550783B2 Turbine blade platform undercut 有权
标题翻译：涡轮叶片平台底切
公开(公告)号：US08550783B2
公开(公告)日：2013-10-08
申请号：US13078664
申请日：2011-04-01
申请人： Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
发明人： Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/187 , F05D2230/10 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/81 , F05D2270/114
摘要： A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.
摘要翻译：公开了一种延长燃气轮机叶片的使用寿命的系统和方法，其中燃气轮机叶片包括设计成减轻施加到翼型后缘的基座区域中的机械和热应力的底切构型。本发明的实施例包括具有不同后缘底切构造的涡轮叶片构造以及供应到涡轮叶片的后缘区域的内部通道的附加冷却。

89. 发明申请

US20130209236A1 GAS TURBINE ENGINE COMPONENT WITH COMPOUND CUSP COOLING CONFIGURATION 有权
标题翻译：气体涡轮发动机组件与组合CUSP冷却配置
公开(公告)号：US20130209236A1
公开(公告)日：2013-08-15
申请号：US13544227
申请日：2012-07-09
申请人： JinQuan Xu
发明人： JinQuan Xu
IPC分类号： F01D25/12 , F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F01D25/24 , F01D25/30 , F02C3/04 , F04D29/324 , F04D29/522 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/70 , F05D2250/71 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.
摘要翻译：一种用于燃气涡轮发动机的部件，其包括具有第一表面和第二表面的气体通道壁。冷却孔从第一表面中的入口穿过气体通道壁延伸穿过第二表面中的出口。尖峰形成在过渡处。

90. 发明申请

US20130209232A1 MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS 审中-公开
标题翻译：具有热障涂层的气体涡轮发动机组件中的多孔冷却孔
公开(公告)号：US20130209232A1
公开(公告)日：2013-08-15
申请号：US13543932
申请日：2012-07-09
申请人： JinQuan Xu , Edward F. Pietraszkiewicz , Mark F. Zelesky , Glenn Levasseur , Dominic J. Mongillo
发明人： JinQuan Xu , Edward F. Pietraszkiewicz , Mark F. Zelesky , Glenn Levasseur , Dominic J. Mongillo
IPC分类号： F01D5/18 , F01D9/02 , B05D3/06 , B05D7/00 , B05D3/14
CPC分类号： B24C1/045 , B23K26/0622 , B23K26/082 , B23K26/146 , B23K26/389 , B23K2101/001 , B26F3/004 , F01D5/186 , F01D5/288 , F01D9/041 , F05D2240/81 , F05D2250/52 , F05D2250/70 , F05D2260/202 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676 , Y02T50/6765
摘要： A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.
摘要翻译：燃气涡轮发动机部件包括具有内表面和外皮的壁。多个冷却空气孔从内表面延伸到外皮。冷却孔包括合并到计量部分中的入口和在计量部分下游的扩散部分，并延伸到外皮的出口。扩散部分包括多个凸角。在外皮上形成涂层，其中多个裂片的至少一部分形成在热障涂层内。还公开了一种形成这种部件的方法。

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