公开(公告)号：US20070177981A1

公开(公告)日：2007-08-02

申请号：US11340577

申请日：2006-01-27

申请人： Thomas Vandeputte ,  John Greene ,  Peter Selent ,  Linda Farral ,  Sze Bun Chan ,  Brian Arness

发明人： Thomas Vandeputte ,  John Greene ,  Peter Selent ,  Linda Farral ,  Sze Bun Chan ,  Brian Arness

IPC分类号： B64C27/46

CPC分类号： F01D5/141 ,  F05D2240/128 ,  F05D2250/74 ,  Y10S416/02

摘要： First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.

摘要翻译： 用于涡轮机的第一级定子叶片包括基本上按照表I中以英寸为单位的X，Y和Z的笛卡尔坐标值的翼型分布，其定义了形成标称轮廓的多个径向间隔的轮廓部分。 每个轮廓截面的Z坐标值是从涡轮机轴线到围绕围绕轮廓部分的轴线的旋转表面的一部分的径向距离。 每个轮廓截面的X和Y值是坐标值，当通过平滑的连续弧连接时，沿着旋转部分的表面限定翼型轮廓部分。 径向隔开的轮廓部分彼此平滑地连接以形成标称翼型轮廓。

公开(公告)号：US20050111969A1

公开(公告)日：2005-05-26

申请号：US10716449

申请日：2003-11-20

申请人： Brian Arness ,  John Greene ,  Linda Farral ,  Sze Bun Chan

发明人： Brian Arness ,  John Greene ,  Linda Farral ,  Sze Bun Chan

IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D1/02

CPC分类号： F01D9/042 ,  F01D25/246 ,  F05D2230/64 ,  F05D2230/80

摘要： Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventing axial removal thereof. To remove a selected nozzle segment, inner diameter retention plate segments and selected retention plate segments are removed, the latter exposing the ends of the pins for axial withdrawal. Upon removal of a predetermined number of pins, the nozzle segments adjacent the selected segment are displaced away from the latter segment to open a gap between the selected segment and adjacent segments whereby the selected segment can be removed in an axial direction.

摘要翻译： 喷嘴段通过在喷嘴段的外带和保持环之间大致轴向延伸的防旋转销固定到保持环以防止圆周旋转。 保持板段覆盖销的端部，防止其轴向移除。 为了去除所选择的喷嘴段，去除内径保持板段和选定的保持板段，后者将引脚的端部暴露以用于轴向退出。 在移除预定数量的销之后，与所选择的段相邻的喷嘴段从后段移开，以打开选定段和相邻段之间的间隙，从而可以沿轴向移除所选段。

公开(公告)号：US20050123388A1

公开(公告)日：2005-06-09

申请号：US10728198

申请日：2003-12-04

申请人： Sze Brian Chan ,  John Greene ,  Linda Farral

发明人： Sze Brian Chan ,  John Greene ,  Linda Farral

IPC分类号： F01D9/02 ,  F01D9/04 ,  F01D9/06 ,  F01D11/00 ,  F01D25/24 ,  F01D1/00

CPC分类号： F01D9/06 ,  F01D9/041

摘要： A turbine nozzle includes, in an exemplary embodiment, an outer band portion, an inner band portion at least one nozzle vane extending between the inner band portion and the outer band portion, and at least one cooling channel extending axially at least partially through at least one of the outer band portion and the inner band portion. The at least one nozzle vane, the inner band portion, and the outer band portion define a flowpath for flowing hot gases of combustion. Each cooling channel includes at least one inlet with each inlet isolated from the flowing hot gases of combustion.

摘要翻译： 涡轮喷嘴在一个示例性实施例中包括外带部分，内带部分，至少一个在内带部分和外带部分之间延伸的喷嘴叶片，以及至少一个冷却通道，至少部分地至少部分延伸至少 外带部分和内带部分中的一个。 至少一个喷嘴叶片，内带部分和外带部分限定了用于流动热的燃烧气体的流路。 每个冷却通道包括至少一个入口，每个入口与流动的热的燃烧气体隔离。

公开(公告)号：US06505326B1

公开(公告)日：2003-01-07

申请号：US09676439

申请日：2000-09-29

申请人： Christopher J. Farral ,  Linda Farral ,  David M. Johnson ,  Mullahalli V. Srinivas

发明人： Christopher J. Farral ,  Linda Farral ,  David M. Johnson ,  Mullahalli V. Srinivas

IPC分类号： G06F1750

CPC分类号： G06F17/5018 ,  G06F2217/80

摘要： A system and method for analyzing a baseline geometry and, optionally, a modified geometry. The method can include generating a numerical representation of a baseline geometry having baseline elements identified with first identifiers or element identifiers, and then assigning second identifiers or analyzer identifiers to the elements. Thermal characteristics of the geometry are analyzed with reference to the second or analyzer identifiers. The results of the thermal analysis can be provided as an input for a structural analysis of the baseline geometry. At least one of the elements of the geometry can then be altered in a manner that at least partially automatically adjusts the surrounding geometry, and the same first identifier or element identifier is associated with the altered element as was associated with the baseline, unaltered element. The altered geometry can be analyzed with respect to a third identifier (or another analyzer identifier) and a correspondence between the identifiers, the baseline element, and the altered element can be established and maintained. Accordingly, the boundary conditions and/or the mesh applied to the baseline geometry can be automatically applied to the altered geometry by referring to the first or element identifiers. Therefore, the time and effort required to analyze the altered geometry can be reduced when compared to the effort typically required by conventional methods.

摘要翻译： 用于分析基准几何和可选地修改的几何的系统和方法。 该方法可以包括生成具有由第一标识符或元素标识符标识的基准元素的基线几何的数值表示，然后将第二标识符或分析器标识符分配给元素。 参考第二个或分析仪标识符分析几何的热特性。 热分析的结果可以作为基准几何结构分析的输入。 然后可以以至少部分地自动调整周围几何形状的方式改变几何元素中的至少一个元素，并且将相同的第一标识符或元素标识符与已改变的元素相关联，如与基准未改变的元素相关联。 可以相对于第三标识符（或另一个分析器标识符）分析改变的几何形状，并且可以建立和维护标识符，基线元素和改变的元素之间的对应关系。 因此，应用于基线几何的边界条件和/或网格可以通过参考第一或元素标识符来自动地应用于改变的几何。 因此，与常规方法通常需要的努力相比，可以减少分析改变的几何形状所需的时间和精力。

公开(公告)号：US20080101925A1

公开(公告)日：2008-05-01

申请号：US11586766

申请日：2006-10-26

申请人： Craig Humanchuk ,  Craig Bielek ,  Linda Farral ,  Glen MacMillan

发明人： Craig Humanchuk ,  Craig Bielek ,  Linda Farral ,  Glen MacMillan

IPC分类号： F03B11/02

CPC分类号： F01D9/041 ,  F05D2250/74

摘要： The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. 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I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，Z值沿喷嘴堆叠轴线与涡轮机半径一致的英寸 。 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：US07527473B2

公开(公告)日：2009-05-05

申请号：US11586766

申请日：2006-10-26

申请人： Craig Humanchuk ,  Craig Bielek ,  Linda Farral ,  Glen MacMillan

发明人： Craig Humanchuk ,  Craig Bielek ,  Linda Farral ,  Glen MacMillan

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F05D2250/74

摘要： The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I. The X and Y values are in inches and the Z value is in inches along the nozzle stacking axis coincident with a turbine radius. 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I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，Z值沿喷嘴堆叠轴线与涡轮机半径一致的英寸 。 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。