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公开(公告)号：US20170002669A1
公开(公告)日：2017-01-05
申请号：US15113062
申请日：2014-11-03
CPC分类号： F01D5/3038 , F01D9/042 , F01D11/008 , F01D25/246 , F05D2220/32 , F05D2260/30 , F05D2300/171 , F05D2300/501 , F05D2300/505 , F05D2300/603
摘要： A mechanical fastening system for rotating or stationary components such as turbine or compressor blades on a rotor or a shaft or a casing, respectively, is disclosed. The system includes a circumferential mounting groove adapted for receiving root sections of the rotating or stationary components as well as intermediate fastening components for fixation of the components in equidistance positions. The intermediate fastening components comprise at least an upper platform and at least a side plate having a groove for mounting on said rotor. The intermediate fastening components are made of a plurality of distinct parts of different materials from which at least one clamping part is made of or comprises a shape memory alloy or similar material having a pseudo-elasticity behavior.
摘要翻译： 公开了一种用于分别在转子或轴或壳体上的旋转或静止部件如涡轮机或压缩机叶片的机械紧固系统。 该系统包括适于容纳旋转或静止部件的根部的圆周安装凹槽以及用于将部件固定在等距位置的中间紧固部件。 中间紧固部件包括至少一个上部平台和至少一个具有用于安装在所述转子上的凹槽的侧板。 中间紧固部件由不同材料的多个不同部分制成，至少一个夹紧部分由其形成或包括具有假弹性行为的形状记忆合金或类似材料。
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22.发明授权公开(公告)号：US09518478B2
公开(公告)日：2016-12-13
申请号：US14064867
申请日：2013-10-28
CPC分类号： F01D25/12 , F01D9/04 , F01D11/003 , F01D11/005 , F01D11/008 , F05D2240/11 , F05D2240/57
摘要： A gas turbine stator component includes a composite, segmented ring made up of an annular array of arcuate segments, each having end faces formed with respective seal slots, with radial gaps formed between opposed end faces of adjacent arcuate segments. A seal is located between each pair of opposed seal slots to thereby seal the gaps, and a channel is provided in each of said arcuate segments adapted to be supplied with cooling air, the channel connecting to a passage extending between the channel and a respective one of the seal slots or radial gaps, on a lower-pressure side of the seal.
摘要翻译： 燃气涡轮机定子部件包括由圆弧段的环形阵列组成的复合分段环，每个圆形段具有形成有相应密封槽的端面，在相邻弧形段的相对端面之间形成径向间隙。 密封件位于每对相对的密封槽之间，从而密封间隙，并且在每个所述弧形段中设置有适于被供应冷却空气的通道，所述通道连接到在通道和相应的密封槽之间延伸的通道 的密封槽或径向间隙，位于密封件的低压侧。
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公开(公告)号：US20160348525A1
公开(公告)日：2016-12-01
申请号：US14726722
申请日：2015-06-01
发明人： Lane Thornton
CPC分类号： F01D11/006 , F01D5/147 , F01D5/22 , F01D5/225 , F01D11/00 , F01D11/005 , F01D11/008 , F05D2220/32 , F05D2240/55 , F05D2240/80 , F05D2260/941 , F05D2300/173 , F05D2300/174 , F05D2300/177
摘要： A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
摘要翻译： 用于涡轮机翼型件（例如，叶片或叶片）组件的平台后缘密封件包括构造成延伸到限定在周向相邻的一对涡轮机翼型平台之间的配合间隙的后部的主体，以最小化进入叶片 - 通过叶片间隙的后部分的叶片腔。
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公开(公告)号：US20160194973A1
公开(公告)日：2016-07-07
申请号：US14909471
申请日：2014-08-06
发明人： Andrew G. Alarcon
CPC分类号： F01D11/008 , F01D5/02 , F01D5/3007 , F02K3/06 , F05D2220/32 , F05D2240/80 , Y02T50/672 , Y02T50/673
摘要： A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.
摘要翻译： 用于燃气涡轮发动机的平台具有外表面和内表面。 内表面设置有用于将平台安装到转子的安装位置。 平台从前缘延伸到后缘，并在吸力壁和压力壁之间延伸。 在吸入壁和压力壁之间限定圆周方向。 一个突出部从平台向周向外伸出一个吸力壁和压力壁。 当安装平台时，突片具有周向最外部的部分，该部分将邻接相邻平台的内表面。 还公开了风扇部分和燃气涡轮发动机。
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公开(公告)号：US20160186591A1
公开(公告)日：2016-06-30
申请号：US14587714
申请日：2014-12-31
CPC分类号： F01D11/008 , F01D5/3007 , F04D29/164 , F04D29/321 , F04D29/322 , F04D29/329 , Y02T50/671 , Y02T50/673
摘要： A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.
摘要翻译： 一种具有流路的燃气轮机，其具有转子组件，该转子组件包括：第一转子轮，其支撑具有限定所述流路内边界的第一轴向部分的平台的第一转子叶片; 支撑第二转子叶片的第二转子轮，所述第二转子叶片具有限定所述流动路径的内边界的第二轴向部分的平台; 以及环形填料，其包括外侧表面，所述外侧表面限定出现在所述流动路径的内边界的所述第一轴向部分和所述第二轴向部分之间的所述流动路径的内边界的第三轴向部分的至少一部分。 第一转子轮可以包括用于轴向接合形成在第一转子叶片的径向最内表面上的配合表面的轴向连接器和形成在环形填料的径向最内表面上的配合表面。
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公开(公告)号：US20160069217A1
公开(公告)日：2016-03-10
申请号：US14843459
申请日：2015-09-02
发明人： Pierangelo DUÓ , Karl SCHREIBER
CPC分类号： F01D25/28 , F01D5/02 , F01D5/027 , F01D5/12 , F01D5/30 , F01D5/3015 , F01D5/323 , F01D5/326 , F01D9/02 , F01D11/00 , F01D11/008 , F02C7/04 , F05D2220/323 , F05D2230/60 , F05D2240/128 , F05D2240/55 , Y02T50/671
摘要： An aircraft gas turbine with a fan disc at which fan blades 31, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, characterized in that the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped
摘要翻译： 一种具有风扇盘的飞机燃气轮机，其上分布有围绕圆周并形成彼此之间的中间空间的风扇叶片31，其上安装有密封盘，该密封盘布置在风扇盘的背面，并且具有 入口锥体，其安装在风扇盘的前侧，以及布置在中间空间中的填充元件，其特征在于，所述入口锥体包括条形凸耳，所述凸耳与所述入口锥体相同并且其中 可以插入中间空间，其自由端插入形成在密封盘上的环形槽中，并且填充元件布置在每个带状
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公开(公告)号：US20160061048A1
公开(公告)日：2016-03-03
申请号：US14779841
申请日：2014-03-24
CPC分类号： F01D11/008 , F01D5/02 , F01D5/147 , F01D11/006 , F01D15/12 , F05D2220/30 , F05D2240/30 , F05D2240/55 , F05D2250/71 , F05D2250/75 , F05D2260/97
摘要： A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a down stream leg that extends substantially along the downstream surface.
摘要翻译： 相对于轴线布置的涡轮发动机组件包括转子叶片和具有L形几何形状的羽毛密封件。 转子叶片包括翼型件和底座。 翼型件在上游前缘和下游后缘之间轴向延伸，并从底座径向延伸。 底座包括一个颈部和一个口袋。 颈部轴向延伸到下游表面。 口袋横向延伸到颈部。 羽毛密封件横向延伸到袋中，并且包括基本上沿着下游表面延伸的下游腿。
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公开(公告)号：US09194238B2
公开(公告)日：2015-11-24
申请号：US13687027
申请日：2012-11-28
CPC分类号： F01D5/22 , F01D5/284 , F01D5/3007 , F01D5/3084 , F01D11/008 , F01D25/06 , F05D2250/11 , F05D2250/132 , F05D2250/241 , F05D2260/96 , F05D2300/20 , F05D2300/2112 , F05D2300/2114 , F05D2300/2118 , F05D2300/2261 , F05D2300/2283 , F05D2300/6033
摘要： A system for damping vibrations in a turbine includes a first rotating blade having a first ceramic airfoil, a first ceramic platform connected to the first ceramic airfoil, and a first root connected to the first ceramic platform. A second rotating blade adjacent to the first rotating blade includes a second ceramic airfoil, a second ceramic platform connected to the second ceramic airfoil, and a second root connected to the second ceramic platform. A non-metallic platform damper has a first position in simultaneous contact with the first and second ceramic platforms.
摘要翻译： 一种用于阻尼涡轮机振动的系统包括具有第一陶瓷翼型件的第一旋转叶片，连接到第一陶瓷翼型件的第一陶瓷平台和连接到第一陶瓷平台的第一根部。 与第一旋转叶片相邻的第二旋转叶片包括第二陶瓷翼型件，连接到第二陶瓷翼型件的第二陶瓷平台和连接到第二陶瓷平台的第二根部。 非金属平台阻尼器具有与第一和第二陶瓷平台同时接触的第一位置。
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公开(公告)号：US20150132134A1
公开(公告)日：2015-05-14
申请号：US14400929
申请日：2014-02-21
发明人： James R. Murdock
CPC分类号： F01D25/28 , B29C45/0005 , B29K2077/00 , B29K2079/085 , B29K2105/12 , B29L2031/08 , F01D5/225 , F01D5/282 , F01D11/008 , F05D2220/32 , F05D2220/36 , F05D2240/90 , F05D2260/30 , F05D2260/36 , F05D2300/43 , F05D2300/603
摘要： A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.
摘要翻译： 用于燃气涡轮发动机的风扇平台可以包括在第一侧和第二侧之间延伸的外部流动路径表面。 内表面在第一侧和第二侧之间延伸，并且面向径向相对的外流路表面。 多个平台钩可以从内表面径向向内延伸。
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公开(公告)号：US20150104315A1
公开(公告)日：2015-04-16
申请号：US14401004
申请日：2014-02-13
发明人： Royce E. Tatton
CPC分类号： F01D11/008 , F01D5/3007 , F01D5/3053 , F01D11/006 , F04D29/083 , F04D29/322 , F05D2220/36 , F05D2240/80 , Y02T50/673
摘要： A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.
摘要翻译： 公开了一种燃气涡轮发动机，燃气轮机的风扇部和燃气轮机的风扇部的组装方法。 风扇部分可以包括具有狭槽的风扇轮毂，具有cast形旋转器密封件的旋转器，包括从根部延伸到尖端的翼型的风扇叶片，其中所述翼型件具有前缘并且所述根部被容纳在所述槽中， 以及安装在风扇轮毂上且布置在相邻风扇叶片之间的平台。 风扇部分还可以包括翼片密封件，其具有固定到平台侧面的基部，以及与基部一体并且从基部延伸并且朝向根部倾斜并与叶片接合的翼片，密封件从 机翼。
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