公开(公告)号：US07329093B2

公开(公告)日：2008-02-12

申请号：US11340577

申请日：2006-01-27

申请人： Thomas W. Vandeputte ,  John E. Greene ,  Peter C. Selent ,  Linda J. Farral ,  Sze Bun Brian Chan ,  Brian P. Arness

发明人： Thomas W. Vandeputte ,  John E. Greene ,  Peter C. Selent ,  Linda J. Farral ,  Sze Bun Brian Chan ,  Brian P. Arness

IPC分类号： F01D9/00

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：US07029228B2

公开(公告)日：2006-04-18

申请号：US10728198

申请日：2003-12-04

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

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

IPC分类号： F01D25/12

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：US08043061B2

公开(公告)日：2011-10-25

申请号：US11892355

申请日：2007-08-22

申请人： Tony Chiurato ,  Sze Bun Brian Chan ,  Bogdan Razvan Raica ,  Samar Barua ,  Jacob Charles Perry, II

发明人： Tony Chiurato ,  Sze Bun Brian Chan ,  Bogdan Razvan Raica ,  Samar Barua ,  Jacob Charles Perry, II

IPC分类号： F01D5/22

CPC分类号： F01D5/225 ,  F05D2250/74 ,  Y02T50/673

摘要： A turbine bucket includes a bucket airfoil having a tip shroud with a leading edge comprising two scalloped faces and a trailing edge comprising a third scalloped face defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 1-41 set forth in Table I. The X and Y values are distances in inches which, when respective points are connected by smooth, continuing arcs define the leading and trailing edge tip shroud scalloped profiles. The tip shroud further has first and second, upper and lower, Z form edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 42-59 and 60-77, respectively of Table II.

摘要翻译： 涡轮机桶包括具有尖端护罩的铲斗翼型件，其顶端包括两个扇形面，后缘包括基本上按照X和Y的笛卡尔坐标值作为点1-41定义前缘和后缘轮廓的第三扇形面 X和Y值是以英寸为单位的距离，当各个点通过平滑连接时，连续的弧线限定了前缘和后缘尖端护罩扇形轮廓。 尖端罩还具有基本上按照表II的点42-59和60-77的X和Y的笛卡尔坐标值的第一和第二，上和下Z形边缘轮廓。

公开(公告)号：US07988420B2

公开(公告)日：2011-08-02

申请号：US11882531

申请日：2007-08-02

申请人： Brian Peter Arness ,  Tony A Chiurato ,  Sze Bun Brian Chan ,  Bogdan Razvan Raica ,  Samar Barua ,  Jacob Charles Perry, II

发明人： Brian Peter Arness ,  Tony A Chiurato ,  Sze Bun Brian Chan ,  Bogdan Razvan Raica ,  Samar Barua ,  Jacob Charles Perry, II

IPC分类号： B64C27/46 ,  B64C27/473 ,  F01D5/14

CPC分类号： F01D5/141 ,  F01D5/142 ,  F05D2250/74 ,  Y02T50/673 ,  Y10S416/02

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 envelope of +/−.0.040 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按照X表示的X，Y和Z'的笛卡尔坐标值的翼型，其中X和Y值以英寸计，Z'值是从0到1可转换为Z的无量纲值 通过将Z'值乘以翼型件的高度（英寸），以英寸为单位。 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位于垂直于翼面表面方向的+/- 0.040英寸的包络内。

公开(公告)号：US07476084B1

公开(公告)日：2009-01-13

申请号：US11476096

申请日：2006-06-28

申请人： Sze Bun Brian Chan ,  Babu Santhana Gopalakrishnan ,  William Scott Zemitis

发明人： Sze Bun Brian Chan ,  Babu Santhana Gopalakrishnan ,  William Scott Zemitis

IPC分类号： F01D5/30

CPC分类号： F01D5/3007 ,  F01D5/147 ,  F05D2230/10 ,  F05D2240/80 ,  F05D2260/94 ,  F05D2260/941

摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

摘要翻译： 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。 多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。 为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡 燃气轮机叶片的机械性能。 从材料去除区域去除材料会最大化平衡。

公开(公告)号：US07094025B2

公开(公告)日：2006-08-22

申请号：US10716449

申请日：2003-11-20

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

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

IPC分类号： F04D29/44

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。