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1. 发明申请

US20180112536A1 PARTIALLY WRAPPED TRAILING EDGE COOLING CIRCUITS WITH PRESSURE SIDE IMPINGEMENTS 审中-公开
公开(公告)号：US20180112536A1
公开(公告)日：2018-04-26
申请号：US15334517
申请日：2016-10-26
申请人： General Electric Company
发明人： David Wayne Weber , Brendon James Leary
IPC分类号： F01D5/18 , F01D9/06
CPC分类号： F01D5/186 , F01D5/187 , F01D9/065 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202
摘要： A turbine blade airfoil including various internal cavities that are fluidly coupled is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil. The first pressure side cavity may receive a coolant. The airfoil may also include a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, and at least one channel positioned between and fluidly coupling the first and second pressure side cavities. The channel may be positioned radially between a top surface and a bottom surface of the first and second pressure side cavities. Additionally, the airfoil may include a trailing edge cooling system positioned adjacent a trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may receive a portion of the coolant from the first pressure side cavity.

2. 发明申请

US20180094644A1 AIRFOIL SHAPE FOR ELEVENTH STAGE COMPRESSOR STATOR VANE 审中-公开
公开(公告)号：US20180094644A1
公开(公告)日：2018-04-05
申请号：US15286556
申请日：2016-10-05
申请人： General Electric Company
发明人： Prabakaran Modachur Krishnan , Dwight Eric Davidson
IPC分类号： F04D29/54 , F04D29/32 , F04D29/38 , F02C3/04
CPC分类号： F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/3216 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

3. 发明授权

US09932842B2 Structural guide vane leading edge 有权
公开(公告)号：US09932842B2
公开(公告)日：2018-04-03
申请号：US14776382
申请日：2014-03-12
申请人： United Technologies Corporation
发明人： Thomas B. Hyatt , Carl Brian Klinetob
IPC分类号： F01D5/28 , F01D25/00 , F01D5/14 , F01D5/16 , F01D25/16 , F02C7/20
CPC分类号： F01D5/288 , F01D5/147 , F01D5/16 , F01D25/005 , F01D25/007 , F01D25/162 , F02C7/20 , F05D2220/32 , F05D2220/36 , F05D2230/90 , F05D2240/121 , F05D2240/123 , F05D2240/124 , F05D2300/611 , Y02T50/671 , Y02T50/673
摘要： A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.

4. 发明申请

US20180087524A1 AIRFOIL SHAPE FOR EIGHTH STAGE COMPRESSOR ROTOR BLADE 审中-公开
公开(公告)号：US20180087524A1
公开(公告)日：2018-03-29
申请号：US15277576
申请日：2016-09-27
申请人： GENERAL ELECTRIC COMPANY
发明人： JOHN DAVID STAMPFLI , NANDAKUMAR ALADAHALLI RANGASWAMY
IPC分类号： F04D29/38 , F04D29/32 , F04D29/54 , F02C3/04
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

5. 发明申请

US20180080459A1 AIRFOIL SHAPE FOR THIRTEENTH STAGE COMPRESSOR ROTOR BLADE 审中-公开
公开(公告)号：US20180080459A1
公开(公告)日：2018-03-22
申请号：US15272008
申请日：2016-09-21
申请人： GENERAL ELECTRIC COMPANY
发明人： John David Stampfli , John David Dyer
IPC分类号： F04D29/38 , F04D29/32 , F04D29/54 , F02C3/04
CPC分类号： F02C3/04 , F01D5/141 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

6. 发明申请

US20170058682A1 GAS TURBINE COMPONENTS AND METHODS OF ASSEMBLING THE SAME 审中-公开
标题翻译：气体涡轮机组件及其组装方法
公开(公告)号：US20170058682A1
公开(公告)日：2017-03-02
申请号：US14841056
申请日：2015-08-31
申请人： General Electric Company
发明人： Cody Jermaine Ford , Brad Wilson VanTassel
IPC分类号： F01D5/28 , F01D9/04
CPC分类号： F01D5/288 , F01D9/041 , F05D2220/32 , F05D2230/60 , F05D2230/90 , F05D2240/12 , F05D2240/122 , F05D2240/123 , F05D2240/129 , F05D2240/30 , F05D2240/305 , F05D2260/231 , F05D2300/611
摘要： A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge, a trailing edge, a suction side extending from the leading edge to the trailing edge, and a pressure side extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating applied to the airfoil pressure side such that an uncoated margin is defined on the pressure side at the trailing edge.
摘要翻译：提供燃气轮机部件。燃气轮机部件包括具有前缘，后缘，从前缘延伸到后缘的吸力侧的翼型，以及从前缘向与吸力侧相对的后缘延伸的压力侧。燃气轮机部件还包括施加到翼型压力侧的热障涂层，使得在后缘处的压力侧上限定未涂覆的边缘。

7. 发明申请

US20170051680A1 AIRFLOW INJECTION NOZZLE FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的气流喷射喷嘴
公开(公告)号：US20170051680A1
公开(公告)日：2017-02-23
申请号：US14828544
申请日：2015-08-18
申请人： General Electric Company
发明人： Thomas Lee BECKER, JR. , Craig Miller KUHNE
IPC分类号： F02C9/18
CPC分类号： F02C9/18 , F01D5/18 , F01D9/06 , F01D17/162 , F02C3/13 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2260/606 , F05D2270/10 , Y02T50/673 , Y02T50/676
摘要： An airflow injection nozzle for a stage of airflow injection nozzles located in a turbine section of the gas turbine engine is provided. The airflow injection nozzle includes a leading end positioned opposite of a trailing end, as well as a pressure side positioned opposite of a suction side. The airflow injection nozzle includes an opening positioned on the pressure side oriented generally in a flow direction of the gas turbine engine for injecting a flow of bleed air from a compressor section of the gas turbine engine into the turbine section of the gas turbine engine.
摘要翻译：提供了一种用于位于燃气涡轮发动机的涡轮部分中的气流喷射喷嘴级的气流喷射喷嘴。气流喷射喷嘴包括与后端相对的前端以及与吸力侧相对设置的压力侧。气流喷射喷嘴包括位于通常在燃气涡轮发动机的流动方向上的压力侧上的开口，用于将来自燃气涡轮发动机的压缩机部分的排出气流喷射到燃气涡轮发动机的涡轮部分。

8. 发明申请

US20160169015A1 Steam Turbine Stationary Blade 审中-公开
标题翻译：蒸汽轮机固定刀片
公开(公告)号：US20160169015A1
公开(公告)日：2016-06-16
申请号：US14968272
申请日：2015-12-14
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Koji ISHIBASHI , Susumu NAKANO , Takeshi KUDO
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D25/32 , F05D2220/31 , F05D2230/10 , F05D2230/60 , F05D2240/123 , F05D2240/124
摘要： To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.
摘要翻译：提供一种适于有效地去除液膜的汽轮机固定叶片。一种其中具有中空区域的蒸汽轮机固定叶片，所述蒸汽轮机静叶片包括多个槽，并且沿着弦长度的方向排列成多个槽，所述多个槽与工作流体流动通道连通，并且与中空区域连通，并且沿刀片长度的方向延伸，并且至少一个连接部分设置成使得对于多个槽中的最下游槽中的每一个，并且朝向工作流体流动通道的表面定位成更接近中空区域，并且使得连接部分沿着弦长度的方向连接每个最下游狭槽的两个侧壁表面。

9. 发明申请

US20160146057A1 WATER REMOVAL DEVICE FOR STEAM TURBINE 有权
标题翻译：蒸汽涡轮水分离装置
公开(公告)号：US20160146057A1
公开(公告)日：2016-05-26
申请号：US14903371
申请日：2014-05-12
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Ryo TAKATA , Soichiro TABATA
IPC分类号： F01D25/32 , F01D9/02
CPC分类号： F01D25/32 , F01D9/041 , F05D2220/31 , F05D2240/123 , F05D2250/182 , F05D2250/294 , F05D2250/312 , F05D2250/314
摘要： A hollow portion is formed inside a stator blade. A slit having an inlet opening on a pressure surface of the stator blade facing wet steam flow is formed that communicates with the hollow portion in the axial direction of the stator blade. The hollow portion communicates with a region having a lower pressure than the flow field of the wet steam flow. The pressure in the hollow portion is reduced to introduce water film flow formed from water drops on the pressure surface of the stator blade to the slit. The slit is formed at a downstream side end, in the flow direction of the wet steam flow, of the hollow portion, and the stator blade trailing edge side wall surface of the slit is at an acute angle to a leading edge side reference plane of the pressure side of the stator blade.
摘要翻译：中空部分形成在定子叶片内部。在定子叶片的面对湿蒸汽流的压力表面上具有入口的狭缝形成为与定子叶片的轴向上的中空部分连通。中空部分与具有比湿蒸汽流的流场低的压力的区域连通。缩短中空部的压力，将定子叶片的压力面上的水滴形成的水膜引入狭缝。狭缝形成在中空部分的湿蒸汽流的流动方向的下游侧端部，狭缝的定子叶片后缘侧壁面与前缘侧基准面成锐角定子叶片的压力侧。

10. 发明申请

US20160024943A1 STRUCTURAL GUIDE VANE LEADING EDGE 有权
标题翻译：结构导向帆布领先
公开(公告)号：US20160024943A1
公开(公告)日：2016-01-28
申请号：US14776382
申请日：2014-03-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Thomas B. HYATT , Carl Brian KLINETOB
IPC分类号： F01D5/28 , F01D5/14 , F02C7/20
CPC分类号： F01D5/288 , F01D5/147 , F01D5/16 , F01D25/005 , F01D25/007 , F01D25/162 , F02C7/20 , F05D2220/32 , F05D2220/36 , F05D2230/90 , F05D2240/121 , F05D2240/123 , F05D2240/124 , F05D2300/611 , Y02T50/671 , Y02T50/673
摘要： A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.
摘要翻译：用于燃气涡轮发动机的结构导向叶片具有前缘部分，后缘，压力表面和吸力表面。侵蚀涂层如聚氨酯树脂在压力表面和吸力表面上。叶片的前缘没有侵蚀涂层，是裸金属。叶片形成为在压力表面侧包括多个袋和结合搁架，并且在结合搁架上具有保护由侵蚀涂层保护的盖板的环氧树脂粘合线。

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