-
公开(公告)号：US06739838B1
公开(公告)日：2004-05-25
申请号：US10388476
申请日：2003-03-17
申请人： Craig Allen Bielek , Robert Alan Brittingham , Jeff Brian Thompson , Benjamin Arnette Lagrange , Robert Walter Coign
发明人： Craig Allen Bielek , Robert Alan Brittingham , Jeff Brian Thompson , Benjamin Arnette Lagrange , Robert Walter Coign
IPC分类号： F01D514
CPC分类号： F01D5/141 , F01D5/225 , F05D2240/301 , F05D2240/80 , Y10S416/05
摘要： Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.060 inches in directions normal to the surface of the airfoil.
摘要翻译： 第三级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的机翼型材，其中X和Y值为英寸，Z值为从0到1的可转换为Z距离的无量纲值 将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。 X，Y和Z距离可以作为相同常数或数字的函数来缩放，以提供用于铲斗的放大或缩小的翼型部分。 由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上处于±0.060英寸的包络内。
-
公开(公告)号：US06736599B1
公开(公告)日：2004-05-18
申请号：US10249870
申请日：2003-05-14
IPC分类号： F01D904
CPC分类号： F01D9/02 , F01D5/141 , F05D2200/10 , F05D2240/128 , F05D2240/301 , F05D2250/70
摘要： The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.
摘要翻译： 第一级喷嘴具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的翼型轮廓.X和Y值以英寸为单位，并且Z值沿着与a的一致的喷嘴 - 堆叠轴线是无量纲的 涡轮机半径，并通过将Z值乘以翼型的高度并将根半径添加到结果中，将其与涡轮机轴的英寸距离Z转换成Z距离。 X和Y距离可以是可缩放的，作为相同常数或数字的函数，以提供用于喷嘴的放大或缩小的翼型部分。 由X，Y和Z距离给出的额定翼型在±0.160英寸的范围内。
-
公开(公告)号：US20120121415A1
公开(公告)日：2012-05-17
申请号：US12948361
申请日：2010-11-17
IPC分类号： F01D5/08
CPC分类号： F01D9/02 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.
摘要翻译： 涡轮机包括壳体和布置在壳体内的至少一个涡轮叶片。 至少一个涡轮叶片包括可操作地连接到翼型部分的平台部分。 在平台部分形成冷却腔。 冷却腔包括第一壁，与第一壁相对布置的第二壁，连接第一壁和第二壁的第三壁和连接第一壁和第二壁并与第三壁相对定位的第四壁。 冲击冷却板延伸到冷却腔中并限定内腔部分和外腔部分。 所述冲击冷却板包括至少一个冲击冷却通道，所述至少一个冲击冷却通道被构造和设置成将冲击冷却流引导到所述冷却腔的所述第一，第二，第三和第四壁中的至少一个上。
-
公开(公告)号：US08851845B2
公开(公告)日：2014-10-07
申请号：US12948361
申请日：2010-11-17
CPC分类号： F01D9/02 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.
摘要翻译： 涡轮机包括壳体和布置在壳体内的至少一个涡轮叶片。 至少一个涡轮叶片包括可操作地连接到翼型部分的平台部分。 在平台部分形成冷却腔。 冷却腔包括第一壁，与第一壁相对布置的第二壁，连接第一壁和第二壁的第三壁和连接第一壁和第二壁并与第三壁相对定位的第四壁。 冲击冷却板延伸到冷却腔中并限定内腔部分和外腔部分。 所述冲击冷却板包括至少一个冲击冷却通道，所述至少一个冲击冷却通道被构造和设置成将冲击冷却流引导到所述冷却腔的所述第一，第二，第三和第四壁中的至少一个上。
-
公开(公告)号：US20130177447A1
公开(公告)日：2013-07-11
申请号：US13345777
申请日：2012-01-09
CPC分类号： F01D9/041 , F01D5/188 , F05D2240/81 , F05D2260/201 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323
摘要： The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.
摘要翻译： 本申请提供了一种将冲击冷却组件安装在涡轮喷嘴的翼型件的内平台中的方法。 该方法可以包括以下步骤：将插入件定位在机翼的空腔内，将芯出口盖定位在空腔的开口周围，将冲击气室定位在平台空腔内，将未固定的轴套插入穿过冲击气室的组装端口 并进入插入件的气流腔中，并关闭装配口。
-
公开(公告)号：US08684683B2
公开(公告)日：2014-04-01
申请号：US12956554
申请日：2010-11-30
CPC分类号： F01D25/246 , Y10T29/49243 , Y10T29/49318 , Y10T29/4932 , Y10T29/49323 , Y10T29/49718 , Y10T29/49721 , Y10T29/4973 , Y10T29/49815 , Y10T29/49817 , Y10T29/49963
摘要： A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component.
摘要翻译： 涡轮喷嘴附接组件包括形成有在前向轴向方向上开口的周向槽的外涡轮机部件（护罩或涡轮壳体） 一个包括在内带和外带之间延伸的叶片的喷嘴段，外带设置有一个直立的环形钩，形成有一个在后向轴向方向上延伸并被容纳在周向凹槽中的钩元件。 直立的环形钩和钩元件形成有周向定向的槽。 防旋转块位于周向定向的槽中，并且具有大于周向定向槽的相应周向宽度的周向宽度的防倾翻板基本上覆盖防转块的前表面。 防旋转块和防倾翻板直接固定在外涡轮部件上。
-
公开(公告)号：US20130175357A1
公开(公告)日：2013-07-11
申请号：US13345776
申请日：2012-01-09
申请人： Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
发明人： Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC分类号： F01D11/001 , F05D2240/128 , F05D2260/201
摘要： The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
摘要翻译： 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
-
公开(公告)号：US08944751B2
公开(公告)日：2015-02-03
申请号：US13345776
申请日：2012-01-09
申请人： Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
发明人： Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC分类号： F01D11/001 , F05D2240/128 , F05D2260/201
摘要： The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
摘要翻译： 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
-
公开(公告)号：US08864445B2
公开(公告)日：2014-10-21
申请号：US13345777
申请日：2012-01-09
IPC分类号： F01D9/06
CPC分类号： F01D9/041 , F01D5/188 , F05D2240/81 , F05D2260/201 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323
摘要： The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.
摘要翻译： 本申请提供了一种将冲击冷却组件安装在涡轮喷嘴的翼型件的内平台中的方法。 该方法可以包括以下步骤：将插入件定位在机翼的空腔内，将芯出口盖定位在空腔的开口周围，将冲击气室定位在平台空腔内，将未固定的轴套插入穿过冲击气室的组装端口 并进入插入件的气流腔中，并关闭装配口。
-
公开(公告)号：US08668445B2
公开(公告)日：2014-03-11
申请号：US12905569
申请日：2010-10-15
CPC分类号： F01D9/04
摘要： A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.
摘要翻译： 公开了一种用于涡轮或压缩机的喷嘴。 在一个实施例中，多个叶片中的每一个由外护罩支撑，外护罩包括以端对端关系邻近邻接段设置的多个外护罩段。 每个部分包括穿过其中的孔，其尺寸适于接收叶片延伸套筒。 该系统可以与调制的冷却系统一起使用，并且可以允许改进的大修理。
-
-
-
-
-
-
-
-
-
搜索结果
18 条记录 (耗时 0.025 秒)
