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公开(公告)号：US5536143A
公开(公告)日：1996-07-16
申请号：US414700
申请日：1995-03-31
CPC分类号： F01D5/187 , F05D2260/2212
摘要： In a gas turbine bucket having a shank portion, a radial tip portion and an airfoil having leading and trailing edges and pressure and suction surfaces, and an internal fluid cooling circuit, an improvement wherein the internal fluid cooling circuit has a serpentine configuration including plural radial outflow passages and plural radial inflow passages. The radial outflow passages, in one example, are shaped to have aspect ratios of about 3.3 to 1 and Buoyancy Numbers of 0.80. A method of determining a configuration for steam cooling passages for a bucket stage in a gas turbine is also provided which includes, in one example, the steps of:a) determining combustion gas inlet temperature and mass flow rate of combustion gases passing through the gas turbine stage;b) taking into account Coriolis and buoyancy secondary flow effects in the steam coolant caused by rotation of the bucket stage; andc) configuring the radial outflow coolant passages to have a size and shape sufficient to produce aspect ratios of about 3.3 to 1 and Buoyancy Numbers in the radial outflow passages of 0.80.
摘要翻译： 在具有柄部，径向前端部分和具有前缘和后缘以及压力和吸力表面的翼型和内部流体冷却回路的燃气涡轮机桶中，其中内部流体冷却回路具有包括多个径向的蛇形结构 流出通道和多个径向流入通道。 在一个示例中，径向流出通道被成形为具有约3.3比1的纵横比和<0.15或> 0.80的浮力数。 还提供了一种确定燃气轮机中用于铲斗级的蒸汽冷却通道的构造的方法，在一个示例中包括以下步骤：a）确定通过气体的燃烧气体的燃烧气体入口温度和质量流量 涡轮级; b）考虑由铲斗级旋转引起的蒸汽冷却剂中的科里奥利和浮力二次流动作用; 以及c）将径向流出冷却剂通道配置成具有足以产生约3.3比1的纵横比和径向流出通道中的浮力数<0.15或> 0.80的尺寸和形状。
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公开(公告)号：US20100266410A1
公开(公告)日：2010-10-21
申请号：US12425434
申请日：2009-04-17
申请人： Sergio Daniel Marques Amaral , Michael A. Sullivan , Xiuzhang J. Zhang , Gary M. Itzel , Felipe Roman-Morales , Scott E. Ellis
发明人： Sergio Daniel Marques Amaral , Michael A. Sullivan , Xiuzhang J. Zhang , Gary M. Itzel , Felipe Roman-Morales , Scott E. Ellis
CPC分类号： F01D5/20 , F05D2240/122 , F05D2240/304
摘要： A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.
摘要翻译： 用于燃气涡轮发动机的涡轮转子叶片的叶片尖端，涡轮转子叶片包括翼型件和根部，用于将翼型件沿着径向轴线安装到涡轮机罩内的转子盘，压力侧壁和吸力侧壁 其在前缘和后缘处连接在一起，所述压力侧壁和吸力侧壁从所述根部分延伸到所述叶片尖端，以及形成在所述叶片尖端处的尖叫尖端空腔，所述叶片尖端包括：起始于 尖叫尖端腔，其中后缘沟槽通常朝着叶片尖端的后缘延伸。
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公开(公告)号：US08157504B2
公开(公告)日：2012-04-17
申请号：US12425434
申请日：2009-04-17
申请人： Sergio Daniel Marques Amaral , Michael A. Sullivan , Xiuzhang J. Zhang , Gary M. Itzel , Felipe Roman-Morales , Scott E. Ellis
发明人： Sergio Daniel Marques Amaral , Michael A. Sullivan , Xiuzhang J. Zhang , Gary M. Itzel , Felipe Roman-Morales , Scott E. Ellis
CPC分类号： F01D5/20 , F05D2240/122 , F05D2240/304
摘要： A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.
摘要翻译： 用于燃气涡轮发动机的涡轮转子叶片的叶片尖端，涡轮转子叶片包括翼型件和根部，用于将翼型件沿着径向轴线安装到涡轮机罩内的转子盘，压力侧壁和吸力侧壁 其在前缘和后缘处连接在一起，所述压力侧壁和吸力侧壁从所述根部分延伸到所述叶片尖端，以及形成在所述叶片尖端处的尖叫尖端空腔，所述叶片尖端包括：起始于 尖叫尖端腔，其中后缘沟槽通常朝着叶片尖端的后缘延伸。
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公开(公告)号：US07689493B1
公开(公告)日：2010-03-30
申请号：US11558834
申请日：2006-11-10
申请人： Michael A. Sullivan , Philip Fischer , Philip Galdi , David Shen
发明人： Michael A. Sullivan , Philip Fischer , Philip Galdi , David Shen
IPC分类号： G06Q40/00
CPC分类号： G06Q40/06
摘要： The disclosure details the implementation of apparatuses, methods, and systems for asset index tracking. The disclosure details how an asset index tracker aligns investor asset portfolios to a selected asset index. The asset index tracker enables investors to automatically match their portfolio to a predefined index. The asset index tracker compares the investor's portfolio to the selected index and provides recommendations to rebalance the portfolio at specified intervals. This is achieved by comparing the investor's portfolio to the index to determine the trades necessary to align the portfolio to the index. A correlation and estimated tracking error of the portfolio to the index may be calculated to validate how the portfolio matches the index. The resulting trade recommendations may be executed upon the investor's approval or automatically. The execution of the trades achieves the rebalancing of the investor's portfolio to more closely track a selected target index.
摘要翻译： 本公开详细描述了用于资产索引跟踪的装置，方法和系统的实现。 披露详细介绍了资产指数跟踪器如何将投资者资产组合与所选资产指数进行调整。 资产指数跟踪器使投资者能够将其投资组合自动匹配到预定义的指数。 资产指数跟踪器将投资者的投资组合与所选指数进行比较，并提供以指定时间间隔重新平衡投资组合的建议。 这是通过将投资者的投资组合与指数进行比较来确定将投资组合与指数调整所必需的交易。 可以计算投资组合对指数的相关性和估计跟踪误差，以验证投资组合如何与指数匹配。 所产生的交易建议可以在投资者的批准或自动执行。 该交易的执行实现了投资者投资组合的再平衡，以更紧密地跟踪选定的目标指数。
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公开(公告)号：US5472313A
公开(公告)日：1995-12-05
申请号：US264743
申请日：1994-06-23
申请人： Armando J. Quinones , Harold P. Rieck, Jr. , Richard W. Albrecht , Michael A. Sullivan , Robert H. Weisgerber , Larry W. Plemmons
发明人： Armando J. Quinones , Harold P. Rieck, Jr. , Richard W. Albrecht , Michael A. Sullivan , Robert H. Weisgerber , Larry W. Plemmons
CPC分类号： F04D29/582 , F01D5/082 , F04D29/321 , Y02T50/676
摘要： A turbine disk cooling system for a gas turbine engine of a type having a compressor section including first and second disks connected by a seal and defining a compressor interstage volume, a turbine section including first and second stage disks connected by a seal and defining a turbine inner stage volume, and a compressor shaft interconnecting the compressor disks with the turbine disks including orifices located in the compressor seal for allowing air in the compressor section to enter the compressor interstage volume, and a radial inflow impeller for guiding the compressor air towards the compressor shaft. The impeller including a plurality of radially-extending conduits suspended in the compressor interstage volume, the conduits having a plurality of interior, radially-extending passages for conveying the compressor air from the orifice to the compressor shaft. The cooling system further including ducts concentric with the engine centerline for conveying air from the compressor interstage volume to the turbine section, wherein the first stage turbine disk includes an aft shaft having a plurality of openings therethrough allowing the flow of air from the ducts into the turbine interstage volume. The tubular conduit elements having a radially outer portion divided into a plurality of spaced longitudinal segments and a radially inner portion protruding from the conduit element and including a peripheral flange shaped to engage the peripheral flange of the conduit elements.
摘要翻译： 一种用于具有压缩机部分的燃气涡轮发动机的涡轮盘冷却系统，所述压缩机部分包括通过密封件连接并限定压缩机级间容积的第一和第二盘，涡轮部分，包括通过密封件连接的第一和第二级盘， 以及压缩机轴，其将压缩机盘与包括位于压缩机密封件中的孔的涡轮盘相互连接，以允许压缩机部分中的空气进入压缩机级间容积;以及径向流入叶轮，用于将压缩机空气引导到压缩机 轴。 叶轮包括悬挂在压缩机级间体积中的多个径向延伸的管道，该管道具有多个内部径向延伸的通道，用于将压缩机空气从孔口输送到压缩机轴。 所述冷却系统还包括与所述发动机中心线同心的管道，用于将空气从所述压缩机级间容积输送到所述涡轮部分，其中所述第一级涡轮盘包括具有多个开口的后轴，所述后轴允许从所述管道进入的空气流入 涡轮级间体积。 所述管状导管元件具有分成多个间隔的纵向段的径向外部部分和从所述导管元件突出的径向内部，并且包括成形为接合所述导管元件的周边凸缘的外围凸缘。
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