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公开(公告)号：US20130071249A1
公开(公告)日：2013-03-21
申请号：US13235765
申请日：2011-09-19
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y10S416/02
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型件，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中Z值是来自0的无量纲值 通过将Z值乘以翼型件的高度（英寸）并增加翼型件底座的半径，其中X和Y是以英寸为单位的距离，当通过平滑的连续弧连接时， 在每个距离Z处限定翼型轮廓部分，Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。
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公开(公告)号：US08845296B2
公开(公告)日：2014-09-30
申请号：US13235765
申请日：2011-09-19
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y10S416/02
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型件，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中Z值是来自0的无量纲值 通过将Z值乘以翼型件的高度（英寸）并增加翼型件底座的半径，其中X和Y是以英寸为单位的距离，当通过平滑的连续弧连接时， 在每个距离Z处限定翼型轮廓部分，Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。
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公开(公告)号：US09127560B2
公开(公告)日：2015-09-08
申请号：US13308927
申请日：2011-12-01
CPC分类号： F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.
摘要翻译： 冷却的涡轮叶片包括用于将叶片固定到转子的根部，沿着径向轴线从根部延伸的翼型件，以及设置在翼型件的径向向外端部处的尖端护罩。 尖端护罩从翼型件在圆周方向上延伸，并且在其本身内限定出一个内部集气室和一个周边通风室。 翼型件限定了靠近翼型件的后缘部分的径向延伸穿过翼型件的后翼型件冷却通道。 翼型件还限定了一个后部冷却入口，用于向后翼型冷却通道提供冷却流体的后部流。 翼型件还限定至少一个后冷却出口，用于将后流冷却流体从尾气流冷却通道排出到周边通风室。 尖端罩限定了至少一个周边通风口，用于排出冷却流体的后部流。
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公开(公告)号：US20130142649A1
公开(公告)日：2013-06-06
申请号：US13308927
申请日：2011-12-01
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/2214 , Y02T50/673 , Y02T50/676
摘要： A cooled turbine blade comprises a root for fixing the blade to rotor, an airfoil extending along a radial axis from the root, and a tip shroud disposed at a radially outward end of the airfoil. The tip shroud extends in a circumferential direction from the airfoil and defines, within itself, a core plenum and a peripheral plenum. The airfoil defines an aft airfoil cooling passage that extends radially through the airfoil proximate a trailing edge portion of the airfoil. The airfoil also defines an aft cooling inlet for providing an aft stream of cooling fluid to the aft airfoil cooling passage. The airfoil also defines at least one aft cooling exit for discharging the aft stream of cooling fluid from the aft airflow cooling passage to the peripheral plenum. The tip shroud defines at least one peripheral plenum vent for discharging the aft stream of cooling fluid.
摘要翻译： 冷却的涡轮叶片包括用于将叶片固定到转子的根部，沿着径向轴线从根部延伸的翼型件，以及设置在翼型件的径向向外端部处的尖端护罩。 尖端护罩从翼型件在圆周方向上延伸，并且在其本身内限定出一个内部集气室和一个周边通风室。 翼型件限定了靠近翼型件的后缘部分的径向延伸穿过翼型件的后翼型件冷却通道。 翼型件还限定了一个后部冷却入口，用于向后翼型冷却通道提供冷却流体的后部流。 翼型件还限定至少一个后冷却出口，用于将后流冷却流体从尾气流冷却通道排出到周边通风室。 尖端罩限定了至少一个周边通风口，用于排出冷却流体的后部流。
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公开(公告)号：US08790086B2
公开(公告)日：2014-07-29
申请号：US12944209
申请日：2010-11-11
CPC分类号： F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.
摘要翻译： 涡轮机具有围绕转子设置的叶片组件。 每个叶片组件都具有翼型和铲斗。 口袋被定义在桶的尾部和前侧，其端部具有阻尼器销槽。 后侧的减震器销槽具有足以完全容纳阻尼销的深度。 第一相邻刀片组件的后侧的阻尼器销槽相对于第二相邻刀片组件的前侧处的阻尼器销槽定位，以允许阻尼销移动。 在后侧的袋的每一侧是其中具有密封销的密封销槽。 密封销槽延伸超过在后侧与减震器销槽的内边缘对齐的线，其中密封销与阻尼销重叠。
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6.发明申请TURBINE BUCKET FOR USE IN GAS TURBINE ENGINES AND METHODS FOR FABRICATING THE SAME 审中-公开用于气体涡轮发动机的涡轮马桶及其制造方法公开(公告)号：US20120195742A1
公开(公告)日：2012-08-02
申请号：US13015747
申请日：2011-01-28
CPC分类号： F01D5/225 , F01D11/122 , F05D2250/34 , F05D2250/38
摘要： A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance.
摘要翻译： 用于涡轮发动机的涡轮机桶。 涡轮机桶包括燕尾榫，其连接到位于涡轮机外壳内的转子组件。 一个平台从燕尾榫延伸出来。 机翼从平台延伸。 翼型件包括根端和尖端。 尖端从根端朝向涡轮机壳体向外延伸。 尖端罩从尖端延伸。 尖端护罩包括护罩板。 第一护罩导轨，其从罩板向涡轮机壳体延伸第一径向距离。 第二护栏导轨从罩板朝着与第一径向距离不同的涡轮机壳体延伸第二径向距离。
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公开(公告)号：US08876478B2
公开(公告)日：2014-11-04
申请号：US12948364
申请日：2010-11-17
CPC分类号： F01D5/24 , F01D5/22 , F01D11/006 , F05D2260/96
摘要： A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.
摘要翻译： 用于涡轮机叶片的阻尼器销包括细长主体部分，其具有第一基本上均匀的横截面形状，并且在主体部分的相对端处具有第二相对较小横截面形状的轴向对准的前端部和后端部。 在相对的前端部和后端部之间的一个或两个上设置有密封元件，其径向向外突出超过主体部分。
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公开(公告)号：US07731482B2
公开(公告)日：2010-06-08
申请号：US11423789
申请日：2006-06-13
申请人： Benjamin Arnette Lagrange , Randall Richard Good , Gary Charles Liotta , Jon Robert DeLong , Matthew Durham Collier , James William Vehr , Anthony Aaron Chiurato
发明人： Benjamin Arnette Lagrange , Randall Richard Good , Gary Charles Liotta , Jon Robert DeLong , Matthew Durham Collier , James William Vehr , Anthony Aaron Chiurato
IPC分类号： F01D5/26
CPC分类号： F01D5/22 , F05D2240/80 , F05D2250/70 , Y10S416/50
摘要： A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.
摘要翻译： 一种涡轮叶片的阻尼系统。 阻尼系统包括具有可变切向深度的阻尼口袋和位于阻尼口袋内的阻尼器销。
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公开(公告)号：US20120121423A1
公开(公告)日：2012-05-17
申请号：US12944209
申请日：2010-11-11
IPC分类号： F01D5/26
CPC分类号： F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.
摘要翻译： 涡轮机具有围绕转子设置的叶片组件。 每个叶片组件都具有翼型和铲斗。 口袋被定义在桶的尾部和前侧，其端部具有阻尼器销槽。 后侧的减震器销槽具有足以完全容纳阻尼销的深度。 第一相邻刀片组件的后侧的阻尼器销槽相对于第二相邻刀片组件的前侧处的阻尼器销槽定位，以允许阻尼销移动。 在后侧的袋的每一侧是其中具有密封销的密封销槽。 密封销槽延伸超过在后侧与减震器销槽的内边缘对齐的线，其中密封销与阻尼销重叠。
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公开(公告)号：US20070286734A1
公开(公告)日：2007-12-13
申请号：US11423789
申请日：2006-06-13
申请人： Benjamin Arnette Lagrange , Randall Richard Good , Gary Charles Liotta , Jon Robert DeLong , Matthew Durham Collier , James William Vehr
发明人： Benjamin Arnette Lagrange , Randall Richard Good , Gary Charles Liotta , Jon Robert DeLong , Matthew Durham Collier , James William Vehr
IPC分类号： F03B3/12
CPC分类号： F01D5/22 , F05D2240/80 , F05D2250/70 , Y10S416/50
摘要： A damping system for a turbin bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.
摘要翻译： 用于涡轮桶的阻尼系统。 阻尼系统包括具有可变切向深度的阻尼口袋和位于阻尼口袋内的阻尼器销。
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