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公开(公告)号：US20140030073A1
公开(公告)日：2014-01-30
申请号：US13560042
申请日：2012-07-27
IPC分类号： F01D25/08
CPC分类号： F01D25/12 , F01D9/065 , F05D2250/14 , F05D2250/75
摘要： A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.
摘要翻译： 用于从燃气涡轮机去除热量的系统通常包括在燃气涡轮机内布置成环形阵列的多个固定喷嘴。 多个固定喷嘴中的每一个可以包括径向外部平台和径向延伸的冷却通道。 径向延伸的冷却通道可以具有大致轴向和周向延伸穿过径向外部平台的一部分的入口。 闭环冷却盘管可围绕多个固定喷嘴中的两个或更多个的径向外部平台周向延伸。 闭环冷却盘管可以沿两个或多个固定喷嘴中的每一个的径向延伸的冷却通道的入口周向设置，并且冷却介质可以流过冷却盘管并流出燃气轮机，以便 从燃气轮机去除热量。
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公开(公告)号：US09382810B2
公开(公告)日：2016-07-05
申请号：US13560042
申请日：2012-07-27
CPC分类号： F01D25/12 , F01D9/065 , F05D2250/14 , F05D2250/75
摘要： A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.
摘要翻译： 用于从燃气涡轮机去除热量的系统通常包括在燃气涡轮机内布置成环形阵列的多个固定喷嘴。 多个固定喷嘴中的每一个可以包括径向外部平台和径向延伸的冷却通道。 径向延伸的冷却通道可以具有大致轴向和周向延伸穿过径向外部平台的一部分的入口。 闭环冷却盘管可围绕多个固定喷嘴中的两个或更多个的径向外部平台周向延伸。 闭环冷却盘管可以沿两个或多个固定喷嘴中的每一个的径向延伸的冷却通道的入口周向设置，并且冷却介质可以流过冷却盘管并流出燃气轮机，从而 从燃气轮机去除热量。
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公开(公告)号：US09188012B2
公开(公告)日：2015-11-17
申请号：US13479663
申请日：2012-05-24
CPC分类号： F01D5/20 , F01D5/186 , F05D2260/204
摘要： A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip. The tip includes a tip plate and, disposed along a periphery of the tip plate, a rail. The rail includes a microchannel connected to a coolant source.
摘要翻译： 描述了一种在燃气涡轮发动机中使用的涡轮转子叶片，其包括在外径向边缘处具有尖端的翼型件。 翼型件包括压力侧壁和抽吸侧壁，该侧壁在翼型的前缘和后缘处连接在一起，压力侧壁和吸力侧壁从根部延伸到尖端。 尖端包括尖端板，并且沿着尖端板的周边布置有轨道。 导轨包括连接到冷却剂源的微通道。
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公开(公告)号：US08956104B2
公开(公告)日：2015-02-17
申请号：US13271751
申请日：2011-10-12
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。
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公开(公告)号：US20130336800A1
公开(公告)日：2013-12-19
申请号：US13524055
申请日：2012-06-15
CPC分类号： F01D5/288 , B23H1/00 , B23K1/0018 , B23K31/02 , C23C4/01 , C23C14/042 , F01D5/186 , F05D2230/30 , F05D2230/90 , F05D2260/204
摘要： Various embodiments of the disclosure include a component, methods of forming components, and methods of cooling components. In some embodiments, a component is disclosed including: a body; a microchannel extending through a portion of the body; a thermal barrier coating (TBC) covering a portion of the microchannel; and a marker member extending from the microchannel through the TBC or from an end of the microchannel, the marker member indicating a location of the microchannel in the body.
摘要翻译： 本公开的各种实施例包括部件，形成部件的方法和冷却部件的方法。 在一些实施例中，公开了一种组件，包括：主体; 延伸穿过身体的一部分的微通道; 覆盖微通道的一部分的热障涂层（TBC）; 以及从微通道穿过TBC或从微通道的端部延伸的标记构件，标记构件指示微通道在体内的位置。
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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
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。
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公开(公告)号：US20130313307A1
公开(公告)日：2013-11-28
申请号：US13479710
申请日：2012-05-24
IPC分类号： B23K31/02
CPC分类号： F01D5/187 , F05D2230/232
摘要： A method for manufacturing a cooling passage in a component of a machine is described. The method may include: forming a channel in a surface of the component, the channel having a predetermined configuration; forming a cover wire, the cover wire having a predetermined configuration based on the predetermined configuration of the channel; nesting the cover wire in the channel; and welding the nested cover wire to the component such that the channel is enclosed.
摘要翻译： 描述了一种用于在机器的部件中制造冷却通道的方法。 所述方法可以包括：在所述部件的表面中形成通道，所述通道具有预定的构造; 形成盖线，所述盖线基于所述通道的预定配置具有预定配置; 将盖线嵌入通道中; 并将嵌套的盖线焊接到部件上，使得通道被封闭。
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公开(公告)号：US08539773B2
公开(公告)日：2013-09-24
申请号：US12365382
申请日：2009-02-04
申请人： Willy Steve Ziminsky , Thomas Edward Johnson , Benjamin Paul Lacy , William David York , Jong Ho Uhm , Baifang Zuo
发明人： Willy Steve Ziminsky , Thomas Edward Johnson , Benjamin Paul Lacy , William David York , Jong Ho Uhm , Baifang Zuo
CPC分类号： F23R3/286 , F23D2900/00008 , F23D2900/00012 , F23R3/10 , F23R3/34
摘要： A fuel/air mixing tube for use in a fuel/air mixing tube bundle is provided. The fuel/air mixing tube includes an outer tube wall extending axially along a tube axis between an inlet end and an exit end, the outer tube wall having a thickness extending between an inner tube surface having a inner diameter and an outer tube surface having an outer tube diameter. The tube further includes at least one fuel injection hole having a fuel injection hole diameter extending through the outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back.
摘要翻译： 提供了一种用于燃料/空气混合管束的燃料/空气混合管。 燃料/空气混合管包括沿入口端和出口端之间的管轴线轴向延伸的外管壁，外管壁具有在具有内径的内管表面和外管表面之间延伸的厚度， 外管直径。 该管还包括至少一个具有延伸穿过外管壁的燃料喷射孔直径的燃料喷射孔，燃料喷射孔相对于管轴具有喷射角。 本发明提供了具有低燃烧产生的NOx和低流量压力损失的良好的燃料空气混合，转化为高燃气轮机效率，耐久性，并且耐火焰保持和回闪。
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公开(公告)号：US08499566B2
公开(公告)日：2013-08-06
申请号：US12855156
申请日：2010-08-12
IPC分类号： F02C7/12
摘要： A combustor liner is disclosed. The combustor liner includes an upstream portion, a downstream end portion extending from the upstream portion along a generally longitudinal axis, and a cover layer associated with an inner surface of the downstream end portion. The downstream end portion includes the inner surface and an outer surface, the inner surface defining a plurality of microchannels. The downstream end portion further defines a plurality of passages extending between the inner surface and the outer surface. The plurality of microchannels are fluidly connected to the plurality of passages, and are configured to flow a cooling medium therethrough, cooling the combustor liner.
摘要翻译： 公开了一种燃烧器衬套。 燃烧器衬套包括上游部分，沿着大致纵向轴线从上游部分延伸的下游端部分以及与下游端部分的内表面相关联的覆盖层。 下游端部包括内表面和外表面，内表面限定多个微通道。 下游端部还限定在内表面和外表面之间延伸的多个通道。 多个微通道流体地连接到多个通道，并且构造成使冷却介质流过其中，冷却燃烧器衬套。
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公开(公告)号：US08365532B2
公开(公告)日：2013-02-05
申请号：US12570678
申请日：2009-09-30
申请人： Baifang Zuo , Willy Steve Ziminsky , Thomas Edward Johnson , John Charles Intile , Benjamin Paul Lacy
发明人： Baifang Zuo , Willy Steve Ziminsky , Thomas Edward Johnson , John Charles Intile , Benjamin Paul Lacy
IPC分类号： F02C1/00
CPC分类号： F23D14/62 , F23C2900/07001 , F23D2900/14004 , F23D2900/14701 , F23R3/14 , F23R3/286
摘要： A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow.
摘要翻译： 喷嘴包括入口，出口和轴向中心线。 围绕轴向中心线的护罩从入口延伸到出口并限定圆周。 入口周围的圆周大于入口下游第一点处的圆周，入口下游第一点处的圆周小于第一点下游第二点处的圆周。 用于通过喷嘴供应燃料的方法沿着第一路径引导第一气流和沿着与第一路径分离的第二路径的第二气流。 该方法还包括将燃料喷射到第一路径或第二路径中的至少一个中并且加速第一气流或第二气流中的至少一个。
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