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21.发明授权Turbine nozzle and method for cooling a turbine nozzle of a gas turbine engine 有权涡轮喷嘴和用于冷却燃气涡轮发动机的涡轮喷嘴的方法公开(公告)号：US09562439B2
公开(公告)日：2017-02-07
申请号：US14141789
申请日：2013-12-27
Applicant: General Electric Company
Inventor： Michelle Jessica Iduate , Gregory Thomas Foster , David Wayne Weber
CPC classification number: F01D9/065 , F01D5/186 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/185 , F05D2260/202
Abstract: The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane. The platform may include a first cooling passage and a separate second cooling passage defined therein. The first cooling passage may be configured to direct a first flow of cooling fluid in a first direction, and the second cooling passage may be configured to direct a second flow of cooling fluid in a second direction substantially opposite the first direction. The present application and the resultant patent further provide a method for cooling a turbine nozzle of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮喷嘴。 涡轮喷嘴可以包括第一喷嘴叶片，第二喷嘴叶片和连接第一喷嘴叶片和第二喷嘴叶片的平台。 平台可以包括第一冷却通道和限定在其中的单独的第二冷却通道。 第一冷却通道可以被构造成在第一方向上引导冷却流体的第一流动，并且第二冷却通道可以被配置成在基本上与第一方向相反的第二方向上引导第二冷却流体流。 本申请和所得到的专利还提供了一种用于冷却燃气涡轮发动机的涡轮喷嘴的方法。
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公开(公告)号：US09416670B2
公开(公告)日：2016-08-16
申请号：US14055082
申请日：2013-10-16
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , Michael James Healy
CPC classification number: F01D5/303 , F01D5/3038 , F01D5/32
Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define a first inner surface of the first end piece. The root portion defines a first projection and an opposing second projection of the first end piece. The first projection has an outer profile adapted to project into a first lateral recess of the attachment slot. The second projection has an outer profile adapted to project into a second lateral recess of the attachment slot. A second end piece fits between the first inner surface of the first end piece and a sidewall portion of the attachment slot and includes a platform portion and a root portion. A borehole extends continuously through the first end piece and the second end piece. A fastener configured to engage with a sidewall portion of the attachment slot extends through the borehole.
Abstract translation: 用于固定相邻转子叶片的锁定间隔件组件包括具有平台部分和限定第一端部件的第一内表面的根部部分的第一端部件。 根部分限定第一端部件的第一突出部和相对的第二突出部。 第一突起具有适于突出到附接槽的第一横向凹部中的外轮廓。 第二突起具有适于突出到附接槽的第二横向凹部中的外轮廓。 第二端件装配在第一端件的第一内表面和附接槽的侧壁部分之间，并包括平台部分和根部。 井眼连续延伸穿过第一端件和第二端件。 构造成与附接槽的侧壁部分接合的紧固件延伸穿过钻孔。
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公开(公告)号：US20160169524A1
公开(公告)日：2016-06-16
申请号：US14567753
申请日：2014-12-11
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , Lewis Berkley Davis, JR. , Gregory Thomas Foster , Kaitlin Marie Graham , Krishnakumar Venkataraman
CPC classification number: F23R3/286 , F01D9/06 , F02C7/222 , F23R3/34 , F23R2900/03341
Abstract: Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.
Abstract translation: 本公开的实施例提供了用于燃料和空气的喷射系统。 根据一个实施例，喷射系统可以包括嵌入在涡轮喷嘴的表面内并且位于第一出口和第二出口之间的混合区域，涡轮喷嘴将发电系统的燃烧器与动力的涡轮级分离 其中所述第一出口基本上与所述第二出口相对; 用于通过第一出口将载气输送到混合区的第一注入管道; 和用于通过第二出口将燃料输送到混合区的第二注入管道; 其中所述载气和所述燃料在离开所述第一注射导管和所述第二注射导管时在所述混合区内混合。
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24.发明申请TURBINE NOZZLE AND METHOD FOR COOLING A TURBINE NOZZLE OF A GAS TURBINE ENGINE 有权涡轮喷嘴和用于冷却气体涡轮发动机涡轮喷嘴的方法公开(公告)号：US20150184530A1
公开(公告)日：2015-07-02
申请号：US14141789
申请日：2013-12-27
Applicant: General Electric Company
Inventor： Michelle Jessica Iduate , Gregory Thomas Foster , David Wayne Weber
IPC: F01D9/06
CPC classification number: F01D9/065 , F01D5/186 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/185 , F05D2260/202
Abstract: The present application and the resultant patent provide a turbine nozzle for a gas turbine engine. The turbine nozzle may include a first nozzle vane, a second nozzle vane, and a platform connecting the first nozzle vane and the second nozzle vane. The platform may include a first cooling passage and a separate second cooling passage defined therein. The first cooling passage may be configured to direct a first flow of cooling fluid in a first direction, and the second cooling passage may be configured to direct a second flow of cooling fluid in a second direction substantially opposite the first direction. The present application and the resultant patent further provide a method for cooling a turbine nozzle of a gas turbine engine.
Abstract translation: 本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮喷嘴。 涡轮喷嘴可以包括第一喷嘴叶片，第二喷嘴叶片和连接第一喷嘴叶片和第二喷嘴叶片的平台。 平台可以包括第一冷却通道和限定在其中的单独的第二冷却通道。 第一冷却通道可以被构造成在第一方向上引导冷却流体的第一流动，并且第二冷却通道可以被配置成在基本上与第一方向相反的第二方向上引导第二冷却流体流。 本申请和所得到的专利还提供了一种用于冷却燃气涡轮发动机的涡轮喷嘴的方法。
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公开(公告)号：US20150184520A1
公开(公告)日：2015-07-02
申请号：US14143472
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Brian Denver Potter , Gregory Thomas Foster
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.
Abstract translation: 一种涡轮机叶片，其包括用于冷却剂的翼型件和径向延伸的室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构型。 所述肋构造可以包括：限定近壁流动室的弧形线肋; 以及在所述弯曲肋条和所述外壁中的一个之间延伸的横向肋，以便将所述近壁流动室分成依次层叠的流动通道，每个所述流动通道包括所述弯曲肋条的一段。 一个流动通道的弧形线肋的段可以具有变窄轮廓，其包括从相对端变窄到设置在它们之间的颈部的轮廓。
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Patent Agency Ranking
公开(公告)号：US10598028B2
公开(公告)日：2020-03-24
申请号：US15334471
申请日：2016-10-26
Applicant: General Electric Company
Inventor： Robert Frank Hoskin , David Wayne Weber , Gregory Thomas Foster
Abstract: An edge coupon for an airfoil is provided. The coupon includes: a coupon body including: a coolant feed; an outward leg extending toward an edge of the coupon and fluidly coupled to the coolant feed; a return leg extending away from the edge of the coupon and radially offset from the outward leg along a radial axis of the coupon; a turn for fluidly coupling the outward leg and the return leg; a collection passage fluidly coupled to the return leg; and a coupling region configured to mate with an airfoil body of the airfoil.
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公开(公告)号：US10465527B2
公开(公告)日：2019-11-05
申请号：US15354221
申请日：2016-11-17
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Robert Peter Hanet
Abstract: A core for an airfoil casting, including: a cantilevered core section; and a boss extending from the cantilevered core section to an outer profile of the core.
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公开(公告)号：US10465521B2
公开(公告)日：2019-11-05
申请号：US15334483
申请日：2016-10-26
Applicant: General Electric Company
Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.
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公开(公告)号：US10352176B2
公开(公告)日：2019-07-16
申请号：US15334474
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster
Abstract: A trailing edge cooling system for a multi-wall blade, including: a cooling circuit, including: an outward leg extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a return leg extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a turn for coupling the outward leg and the return leg; wherein the outward leg is radially offset from the return leg along a radial axis of the multi-wall blade.
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公开(公告)号：US10233761B2
公开(公告)日：2019-03-19
申请号：US15334450
申请日：2016-10-26
Applicant: General Electric Company
Inventor： Zachary John Snider , Gregory Thomas Foster , Joseph Anthony Weber , James Fredric Wiedenhoefer
Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
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