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1.发明公开Fillet for use with a turbine rotor blade tip shroud 审中-公开Übergangkonturfürein Deckband an der Spitze einer Gasturbinenrotorschaufel
公开(公告)号：EP2738352A1
公开(公告)日：2014-06-04
申请号：EP13194959.6
申请日：2013-11-28
发明人： Chouhan, Rohit , Bommanakatte, Harish , Soni, Sumeet , Jayana, Srinivasa Govardhan , Kareff, Spencer Aaron
CPC分类号： F01D5/225 , F01D5/143 , F05D2240/307 , F05D2250/74
摘要： A turbine rotor blade is provided. The turbine rotor blade includes an airfoil (46), an airfoil tip, a tip shroud (48), and a fillet (50) about an intersection (58/59) of the airfoil tip and the tip shroud (48). The fillet (50) defines a fillet profile variable about the intersection (58/59) as a function of aerodynamic airflow about the intersection (58/59).
摘要翻译： 提供涡轮转子叶片。 涡轮转子叶片包括翼型件（46），翼型件末端，尖端护罩（48）和围绕翼型件末端和尖端护罩（48）的交叉点（58/59）的圆角（50）。 圆角（50）围绕交点（58/59）定义关于交点（58/59）的圆角轮廓变量作为空气动力学气流的函数。
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公开(公告)号：EP2743453B1
公开(公告)日：2019-05-22
申请号：EP13196951.1
申请日：2013-12-12
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公开(公告)号：EP2617944A3
公开(公告)日：2015-08-26
申请号：EP13151449.9
申请日：2013-01-16
发明人： Chouhan, Rohit , Soni, Sumeet , Smith, Paul Kendall , Jayana, Srinivasa Govardhan , Pierre, Sylvain , Bommanakatte, Harish , Vijayan, Santhosh Kumar , Kareff, Spencer Aaron
CPC分类号： F01D5/225 , F01D5/141 , F01D5/20 , F01D11/02 , F05D2220/31 , F05D2220/32 , F05D2240/307 , F05D2250/20 , F05D2250/73 , Y02T50/671 , Y02T50/673
摘要： Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud (50) having a pressure side portion (152) and a suction side portion (154). The pressure side portion (152) and the suction side portion (154) are divided by a mean camber line (106) of a turbomachine blade, and the pressure side portion (152) has a greater surface area than the suction side portion (154).
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4.发明公开Turbomachine blade tip shroud with parallel casing configuration 审中-公开Turbomaschinenschaufelspitzendeckband平行机Gehäusekonfiguration
公开(公告)号：EP2650476A2
公开(公告)日：2013-10-16
申请号：EP13163003.0
申请日：2013-04-09
发明人： Chouhan, Rohit , Pierre, Sylvain , Siden, Gunnar Leaf , Vijayan, Santhosh Kumar , Cotroneo, Joseph Anthony
摘要： Embodiments of the present invention include a turbomachine having a turbomachine blade (22) and a stationary structural component (23). The turbomachine blade (22) includes a tip shroud (50) having a leading edge portion (54) where the leading edge portion has a first surface. The stationary structural component (23) is disposed about the turbomachine blade (22) and includes a corresponding portion (56) corresponding to the leading edge portion (54) of the tip shroud (50), where the corresponding portion (56) has a second surface, where the first surface and the second surface have generally parallel contours.
摘要翻译： 本发明的实施例包括具有涡轮机叶片（22）和固定结构部件（23）的涡轮机。 涡轮机叶片（22）包括具有前缘部分（54）的尖端护罩（50），其中前缘部分具有第一表面。 固定结构部件（23）围绕涡轮机叶片（22）设置并且包括对应于尖端护罩（50）的前缘部分（54）的对应部分（56），其中对应部分（56）具有 第二表面，其中第一表面和第二表面具有大致平行的轮廓。
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5.发明公开
公开(公告)号：EP2613014A3
公开(公告)日：2016-06-08
申请号：EP12197952.0
申请日：2012-12-19
发明人： Chouhan, Rohit
CPC分类号： F01D11/127 , F01D5/225 , F05D2220/32 , F05D2230/80 , F05D2240/11 , F05D2250/283 , Y10T29/49238
摘要： The present application provides a stage of a gas turbine engine (10). The stage may include a bucket (120), a shroud (170) facing the bucket (120), and a forward step honeycomb seal (200) on the shroud (170). The forward step honeycomb seal (200) includes a forward step portion (220) and one or more linear portions (210, 230). A method of retrofitting a turbine stage is also provided.
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公开(公告)号：EP2743453A1
公开(公告)日：2014-06-18
申请号：EP13196951.1
申请日：2013-12-12
CPC分类号： F01D5/225 , F01D5/16 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： A rotatable blade 20 for use in a turbomachine includes an airfoil portion 32 having a leading edge 40, a trailing edge 42 a radially-inner end and a radially-outer end; a root section 34 at to the radially-inner end of the airfoil portion 32, and a part-span shroud 48 located on the airfoil portion 32 between the root section 34 and the radially-outer end. The part-span shroud 48 decreases in width and thickness from decreasing in width and thickness from the airfoil portion 32 to a contact surface adapted to engage a mating contact surface on a part-span shroud 48 of an adjacent blade 20.
摘要翻译： 用于涡轮机的可旋转刀片20包括具有前缘40的翼型部分32，径向内端和径向外端的后缘42; 位于翼型部分32的径向内端的根部34和位于根部34和径向外端之间的翼型部分32上的部分跨距护罩48。 部分跨度护罩48的宽度和厚度从宽度和厚度从翼型部分32减小到适于接合相邻叶片20的部分跨度护罩48上的配合接触表面的接触表面。
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7.发明公开Stage of a gas turbine engine and corresponding method of retrofitting 审中-公开Stufe eines Gasturbinenkraftwerks undzugehörigesNachrüstverfahren
公开(公告)号：EP2613014A2
公开(公告)日：2013-07-10
申请号：EP12197952.0
申请日：2012-12-19
发明人： Chouhan, Rohit
CPC分类号： F01D11/127 , F01D5/225 , F05D2220/32 , F05D2230/80 , F05D2240/11 , F05D2250/283 , Y10T29/49238
摘要： The present application provides a stage of a gas turbine engine (10). The stage may include a bucket (120), a shroud (170) facing the bucket (120), and a forward step honeycomb seal (200) on the shroud (170). The forward step honeycomb seal (200) includes a forward step portion (220) and one or more linear portions (210, 230). A method of retrofitting a turbine stage is also provided.
摘要翻译： 本申请提供了一种燃气涡轮发动机（10）的级。 平台可以包括铲斗（120），面向铲斗（120）的护罩（170）和护罩（170）上的前进步骤蜂窝密封件（200）。 前进蜂窝状密封件（200）包括前进台阶部分（220）和一个或多个直线部分（210,230）。 还提供了一种改装涡轮级的方法。
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8.发明公开
公开(公告)号：EP2613013A2
公开(公告)日：2013-07-10
申请号：EP12197660.9
申请日：2012-12-18
CPC分类号： F01D11/127 , F01D5/225 , F05D2220/3215 , F05D2240/11 , F05D2250/283 , F05D2250/71
摘要： The present invention provides a stage (100) of a turbine engine (10). The stage (100) may include a bucket (130), a shroud (170) facing the bucket (130), and a contoured honeycomb seal (180) on the shroud (170). The contoured honeycomb seal (180) may include a first step (190) with a first shape and a second step (200) with a contoured shape. A turbine of a gas turbine engine is also provided.
摘要翻译： 本发明提供一种涡轮发动机（10）的级（100）。 平台（100）可以包括铲斗（130），面向铲斗（130）的护罩（170）和护罩（170）上的轮廓的蜂窝密封件（180）。 成型的蜂窝状密封件（180）可以包括具有第一形状的第一台阶（190）和具有轮廓形状的第二台阶（200）。 还提供了一种燃气涡轮发动机的涡轮机。
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9.发明公开Shroud for a turbine, corresponding turbine and method of assembling the same 审中-公开用于涡轮机的护罩，相应的涡轮机及其组装方法
公开(公告)号：EP2672065A3
公开(公告)日：2018-01-24
申请号：EP13170855.4
申请日：2013-06-06
发明人： Chouhan, Rohit , Soni, Sumeet
CPC分类号： F01D5/143 , F01D9/04 , F01D11/12 , F05D2240/11 , F05D2250/38 , F05D2250/71 , F05D2260/6022 , Y10T29/49236 , Y10T29/4932 , Y10T29/49323
摘要： A shroud 56 for a turbine and a method of assembling is provided. The turbine includes a housing 76, a rotatable shaft 46 and a bucket 78 extending outward therefrom. The shroud 56 includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end 112, a second end 114 and a body 116 extending between the first and second ends. The second end includes an arcuate portion 128 to facilitate fluid flow downstream from the bucket. The shroud further includes a seal 60 coupled to the body to facilitate sealing a gap 66 defined between the bucket 78 and the body 116. Corresponding turbine and method of assembling the same are also provided.
摘要翻译： 提供了用于涡轮机的护罩56和组装方法。 涡轮机包括壳体76，可旋转的轴46和从其向外延伸的铲斗78。 护罩56包括联接至壳体的对准构件，其中对准构件包括第一端112，第二端114和在第一端和第二端之间延伸的主体116。 第二端包括弓形部分128以便于流体从桶中向下游流动。 护罩还包括联接到主体的密封件60，以便于密封限定在轮叶78和主体116之间的间隙66.还提供了对应的涡轮机及其组装方法。
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公开(公告)号：EP2740923A1
公开(公告)日：2014-06-11
申请号：EP13194806.9
申请日：2013-11-28
摘要： An exhaust diffuser 150 is provided having a center body 201 having an inlet adapted for coupling to a turbine. The center body 201 has an outer wall 205, and a guide member 210 disposed inside the center body 201. A flow path reducing member 220 is disposed inside the center body 201. The flow path reducing member 220 is configured to be movable into a first position and a second position. The first position is an inactive position having no impact on an exit flow area of the exhaust diffuser 150, and the second position is a deployed position that reduces the exit flow area of the exhaust diffuser 150.
摘要翻译： 设有排气扩散器150，其具有中心体201，该中心体具有适于联接到涡轮机的入口。 中心体201具有外壁205和设置在中心体201内的引导构件210.流路减小构件220设置在中心体201的内部。流路减小构件220构造成可移动到第一 位置和第二个位置。 第一位置是对排气扩散器150的出口流动区域没有影响的非活动位置，并且第二位置是减小排气扩散器150的出口流动面积的展开位置。
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